Airworthiness Directives (AD's)

[Johan van Ravenzwaaij]

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-2313; AD 75-17-11

Airworthiness Directives; Alexander Schleicher Model ASW 15 Gliders

Preamble Information
AGENCY: Federal Aviation Administration, DOT

DATES: Effective August 18, 1975.

Regulatory Information
75-17-11 ALEXANDER SCHLEICHER: Amendment 39-2313. Applies to ASW 15 gliders, serial numbers 15001 thru 15183, certificated in all categories.

Compliance is required within the next ten hours time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time in service from the last inspection until the rudder nose is reinforced in accordance with paragraph (b)(2) of this AD.

To prevent rudder jam due to improper fin-rudder nose clearance, accomplish the following:

(a) Visually inspect the rudder nose for deformation and measure the gap between the fin and rudder. The acceptable gap is between 2 to 3 mm at the lower rudder hinge tapering to an allowable gap of between 1 to 2 mm at the upper end of the vertical fin.

(b) If the measured gap is not within limits, or a deformation of the rudder nose is found, comply with the following:

(1) Reform the rudder nose inward until the gap is within limits by applying heat in accordance with paragraph 1 of the instructions contained in Alexander Schleicher ASW 15 Technical Note 10 dated January 30, 1973, or an FAA-approved equivalent.

(2) Reinforce rudder nose in accordance with paragraph 2 of the instructions contained in Alexander Schleicher ASW 15 Technical Note 10 dated January 30, 1973 and Alexander Schleicher drawing L-272 150.36/37.B1.33, or an FAA-approved equivalent.

This amendment becomes effective August 18, 1975.

Note: This site take no responsebility for the correctness of this AD what so ever.

[Johan van Ravenzwaaij]

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-4871; AD 84-20-01

Airworthiness Directives; ALEXANDER SCHLEICHER Models ASW 15 and ASW 15 B Sailplanes

Preamble Information
AGENCY: Federal Aviation Administration, DOT

DATES: Effective October 1, 1984.

Regulatory Information

84-20-01 ALEXANDER SCHLEICHER: Amendment 39-4871. Applies to Models ASW 15 and ASW 15 B sailplanes, certificated in any category.

Compliance is required as indicated, unless already accomplished.

To prevent elevator bellcrank failure due to fatigue, accomplish the following:

(a) Within the next 10 takeoffs or 25 hours time-in-service, whichever occurs first, unless already accomplished within the last 90 takeoffs or 75 hours time-in-service, and thereafter at intervals of 100 takeoffs or 100 hours time-in-service, whichever occurs first, visually inspect the bellcrank for cracks in accordance with Item 1 of the Instructions of Alexander Schleicher Technical Note No. 21 (TN No. 21), dated November 24, 1981.

(1) If no cracks are found, reconnect and re-rig the rudder following the manufacturer's instructions contained in TN No. 21.

(2) If cracks are found, prior to further flight, replace the bellcrank in accordance with Item 2 of TN No. 21. Use repair instruction "A" of the technical manual for the applicable ASW 15 type sailplane. Thereafter, at intervals of 100 takeoffs or 100 hours time-in- service, whichever occurs first, perform the inspection required by Item 1 above.

(b) In lieu of replacement of the bellcrank, reinforcement of the bellcrank and modifications of the fin spar and root rib may be accomplished in accordance with Item 2 of the action required of Alexander Schleicher Technical Note No. 22 (TN No. 22), dated November 1, 1982. After reinforcement of the bellcrank in accordance with TN No. 22, the repetitive inspection of this AD is no longer required and TN No. 21 is no longer applicable.

The Alexander Schleicher Technical Notes No. 21 dated November 24, 1981, and No. 22 dated November 1, 1982, identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Alexander Schleicher Segelflugzeubau, D-6414 Poppenhausen, Federal Republic of Germany. These documents may also be examined at the Office of Regional Counsel, 12 New England Executive Park, Burlingon, Massachusetts 01803.

Alternate inspections, adjustment of the inspection interval, or other actions which provide an equivalent level of safety must be approved by the Manager, Brussels Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium, telephone 513.38.30.

This amendment becomes effective October 1, 1984.

Note: This site take no responsebility for the correctness of this AD what so ever.

[Johan van Ravenzwaaij]

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39 [60 FR 22499 NO. 88 5/8/95]
Docket No. 91-CE-40-AD; Amendment 39-9216; AD 95-09-12

Airworthiness Directives; Alexander Schleicher Models ASW-12, ASW-15, ASW-15B, and ASW-17 Gliders

Preamble Information
AGENCY: Federal Aviation Administration, DOT
ACTION: Final rule
SUMMARY: This amendment supersedes Airworthiness Directive (AD) 88-11-05, which currently requires repetitively inspecting the wing spar of Alexander Schleicher Models ASW-15 and ASW-15B gliders for wood rot, and replacing any wing spar where wood rot is found. Alexander Schleicher Models ASW-12 and ASW-17 gliders are of a similar type design to Models ASW-15 and ASW-15B gliders, and the Federal Aviation Administration (FAA), in working with the Civil Aviation Authority of Germany, has decided that the actions referenced in AD 88-11-05 should also apply to Models ASW-12 and ASW-17 gliders. The actions specified by this AD are intended to prevent failure of the wing spar caused by wood rot, which, if not detected and corrected, could result in loss of control of the airplane.
DATES: Effective June 9, 1995.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 9, 1995.
ADDRESSES: Service information that applies to this AD may be obtained from Alexander Schleicher GmbH & Company, D-36163, Popppenhausen-Wasserkuppe, Germany; or Eastern Sailplane, Heath Stage Route Shelburne Falls, Massachusetts 01370; telephone (413) 625-6059.
This information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Herman Belderok, Project Officer, Gliders, Small Airplane Directorate, Aircraft Certification Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone (816) 426-6932; facsimile (816) 426-2169.

SUPPLEMENTARY INFORMATION:
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Alexander Schleicher Models ASW- 12, ASW-15, ASW-15B, and ASW-17 gliders was published in the Federal Register on December 19, 1994 (59 FR 65282). The action proposed to supersede AD 88-11-05, Amendment 39-5997, with a new AD that would (1) retain the requirement of repetitively inspecting the wing spar for wood rot on the Models ASW-15 and ASW-15B gliders, and replacing the wing spar if wood rot is found; and (2) extend these repetitive inspections and possible replacement to Models ASW-12 and ASW-17 gliders. Accomplishment of the proposed inspections would be in accordance with either Alexander Schleicher ASW-15 Technical Note (TN) No. 23, dated April 21, 1988; Alexander Schleicher ASW-12 TN No. 4, dated May 10, 1989; or Alexander Schleicher ASW-17 TN No. 12, dated May 8, 1989, as applicable.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA's determination of the cost to the public.

After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD or add any additional burden upon the public than was already proposed.

The compliance time presented in this AD is based upon calendar time instead of hours time- in-service. Rotting of the wood wing box spar is caused by moisture and the condition could exist or develop regardless of whether the glider is in actual operation. For this reason, the FAA has determined that the compliance time of the required AD action should be in calendar time.

The FAA estimates that 50 gliders (7 ASW-12's, 27 ASW-15's, 6 ASW-15B's, and 10 ASW-17's) in the U.S. registry will be affected by this AD, that it will take approximately 6 workhours per glider to accomplish the required action, and that the average labor rate is approximately $60 an hour. Parts cost approximately $110 per glider, and the required core analysis costs $185. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $32,750. This figure is based upon the assumption that no affected glider owner/operator has accomplished the proposed inspection, nor does it account for repetitive inspections. The FAA has no way of determining the number of repetitive inspections an owner/operator may incur.

In addition, AD 88-11-05 currently mandates the same actions that are required by this final rule AD on 33 gliders. With this in mind, the cost impact of the AD upon U.S. operators is reduced $21,615 from $32,750 to $11,135.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption "ADDRESSES".

List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

Section 39.13 - [AMENDED]
2. Section 39.13 is amended by removing AD 88-11-05, Amendment 39-5997, and by adding a new AD to read as follows:

Regulatory Information

95-09-12 ALEXANDER SCHLEICHER: Amendment 39-9216; Docket No. 91-CE-40-AD. Supersedes AD 88-11-05, Amendment 39-5997.

Applicability: Models ASW-12, ASW-15, ASW-15B, and ASW-17 gliders (all serial numbers), certificated in any category.

NOTE 1: This AD applies to each glider identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For gliders that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (g) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any glider from the applicability of this AD.

Compliance: Required initially as follows, and thereafter as indicated in the body of this AD:

1. For Models ASW-12 and ASW-17: Within the next 6 calendar months after the effective date of this AD, unless already accomplished.

2. For Models ASW-15 and ASW-15B: On or before the last day of the 12th calendar month after the last inspection required by AD 88-11-05, Amendment 39-5997.

To prevent failure of the wing spar caused by wood rot, which, if not detected and corrected, could result in loss of control of the glider, accomplish the following:

(a) Visually inspect the wing spar for wood rot in accordance with either Action Paragraphs 1.1 through 1.3 of Alexander Schleicher ASW-12 Technical Note (TN) No. 4, dated May 10, 1989; Action Paragraphs 1.1, 1.2, and 2.1 of Alexander Schleicher ASW-15 TN No. 23, dated April 21, 1988; or Action Paragraphs 1.1 and 1.2 of Alexander Schleicher ASW-17 TN No. 12, dated May 8, 1989, as applicable.

(b) Mark and send wood cores obtained through the inspection specified in paragraph (a) of this AD to a mycology laboratory for microscopical inspection to detect heavy wood destroying fungal infestation in accordance with either Action Paragraph 1.3 of Alexander Schleicher ASW-12 TN No. 4, dated May 10, 1989; Action Paragraph 2.1 of Alexander Schleicher ASW-15 TN No. 23, dated April 21, 1988; or Action Paragraph 1.2 of Alexander Schleicher ASW-17 TN No. 12, dated May 8, 1989, as applicable.

(c) If moisture damage, swelling, evidence that water has penetrated into the spar fork, or fungal infestation is found, prior to further flight after the inspection required by paragraph (a) of this AD, accomplish the following:

(1) Wait for the results of the microscopical examination and then obtain a repair scheme from the manufacturer through the Manager, Small Airplane Directorate, at the address specified in paragraph (g) of this AD, and incorporate this repair scheme.

(2) Apply preservative, strengthen the inspection hole area, and close the hole in accordance with either Action Paragraph 1.4 of Alexander Schleicher ASW-12 TN No. 4, dated May 10, 1989; Action Paragraph 2.2 of Alexander Schleicher ASW-15 TN No. 23, dated April 21, 1988; or Action Paragraph 1.3 of Alexander Schleicher ASW-17 TN No. 12, dated May 8, 1989, as applicable.

(d) If no moisture damage, swelling, evidence that water has penetrated into the spar fork, or fungal infestation is found, accomplish the following:

(1) Prior to further flight after the inspection required by paragraph (a) of this AD, apply preservative, strengthen the inspection hole area, and close the hole in accordance with either Action Paragraph 1.4 of Alexander Schleicher ASW-12 TN No. 4, dated May 10, 1989; Action Paragraph 2.2 of Alexander Schleicher ASW-15 TN No. 23, dated April 21, 1988; or Action Paragraph 1.3 of Alexander Schleicher ASW-17 TN No. 12, dated May 8, 1989, as applicable.

(2) Operation of the glider during the microscopical examination of the wood core is permitted. However, if these examination results reveal heavy wood destroying fungal infestation, prior to further flight after receiving the results, obtain a repair scheme from the manufacturer through the Manager, Small Airplane Directorate, at the address specified in paragraph (g) of this AD, and incorporate this repair scheme.

(e) The inspection requirements specified in paragraphs (a) through (c) of this AD, excluding the wood core microscopical examination requirements, shall be accomplished annually on or before the last day of the 12th calendar month after the last inspection.

(f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the glider to a location where the requirements of this AD can be accomplished.

(g) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, Aircraft Certification Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate.

(h) The inspections required by this AD shall be done in accordance with either Alexander Schleicher ASW-12 Technical Note No. 4, dated May 10, 1989; Alexander Schleicher ASW-15 Technical Note No. 23, dated April 21, 1988; or Alexander Schleicher ASW-17 Technical Note No. 12, dated May 8, 1989, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Alexander Schleicher GmbH & Company, D-36163, Popppenhausen-Wasserkuppe, Germany; or Eastern Sailplane, Heath Stage Route Shelburne Falls, Massachusetts 01370. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment (39-9216) supersedes AD 88-11-05, Amendment 39-5997.

(j) This amendment becomes effective on June 9, 1995.

Federal Register Information
[Federal Register: May 08, 1995 (Volume 60, Number 88)]
[Page 22499]

Note: This site take no responsebility for the correctness of this AD what so ever.