AD 97-09-08

This amendment supersedes Airworthiness Directive AD 82-25-09 which currently requires repetitively inspecting the pilot and co-pilot control wheel sub-assemblies for cracks, and if cracked, modifying the cracked part on the AeroSpace Technologies of Australia, Limited (ASTA), formerly Government Aircraft Factories (GAF) Nomad Models N22S, N22B, and N24A airplanes. This action would retain the repetitive inspection of the pilot and co-pilot control wheel sub-assemblies for cracks, but would include a modification that would terminate the repetitive inspections by replacing or re-working the control wheel sub-assembly with a part of improved design. This superseding action is prompted by cracking in the control wheel sub-assemblies and the manufacture of an improved part that would terminate the repetitive inspection. The actions specified by this AD are intended to prevent failure of the pilot's and co-pilot's control wheels, which, if not detected and corrected, could result in loss of control of the airplane.

Final rule.

97-09-08 AEROSPACE TECHNOLOGIES OF AUSTRALIA (ASTA) (formerly Government Aircraft Factories): Amendment No. 39-10004; Docket No. 95-CE-31-AD; Supersedes AD 82-25-09, Amendment 39-4510.

Applicability: Nomad Models N22S, N22B, and N24A airplanes, all serial numbers, certificated in any category.

NOTE 1: This AD applies to each airplane 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 airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated in the body of this AD, unless already accomplished.

To prevent failure of the pilot's and co-pilot's control wheels, which, if not detected and corrected, could result in loss of control of the airplane, accomplish the following:

(a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, inspect the pilot and co-pilot control wheel sub-assembly (ASTA part number (P/N) 1/N-45-1208) for structural cracking in the area adjacent to the circumferential weld adjoining the shaft spigot to each control wheel back support plate in accordance with the "2. Accomplishment Instructions" section, "Part A - Inspection" paragraphs in Government Aircraft Factories (GAF) Nomad Alert Service Bulletin (SB) AS/B ANMD-27-27, Revision 1, dated November 5, 1982.

(1) If no cracks are visible, repetitively inspect the control wheel sub-assemblies at intervals not to exceed 100 hours TIS in accordance with the "2. Accomplishment Instructions" section, "Part A - Inspection" paragraphs in GAF Nomad Alert SB AS/B ANMD-27-27, Revision 1, dated November 5, 1982 until the accomplishment of paragraph (b) of this AD.

(2) If cracks are visible during any inspection required by this AD, prior to further flight, modify the control wheel sub-assemblies by replacing or re-working the cracked part with parts of improved design (ASTA P/N 2/N-45-1208 or 1/N-03-734 (reworked part) or the FAA approved equivalent) in accordance with the "2. Accomplishment Instructions" section, "Part B - Modification by Replacement or Rework" paragraphs in GAF Nomad Alert SB AS/B ANMD-27-27, Revision 1, dated November 5, 1982.

(b) Upon the accumulation of 300 hours TIS after the effective date of this AD, modify the control wheel sub-assemblies (ASTA P/N 1/N-45-1208) by replacing the assemblies or re-working the assemblies with parts of improved design (ASTA P/N 2/N-45-1208 or P/N 1/N-03-734, respectively or the FAA approved equivalent) in accordance with the "2. Accomplishment Instructions" section, "Part B - Modification by Replacement or Rework" paragraphs in GAF Nomad Alert SB AS/B ANMD-27-27, Revision 1, dated November 5, 1982.

(c) Accomplishment of the modification in paragraph (b) of this AD is considered a terminating action for the repetitive inspections required in this AD.

(d) 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 airplane to a location where the requirements of this AD can be accomplished.

(e) 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, Los Angeles Aircraft Certification Office, FAA, 3960 Paramount Blvd., Lakewood, California, 90712; telephone (562) 627-5224; facsimile (562) 627-5210. The requestshall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from Los Angeles Aircraft Certification Office.

(f) The inspections and modifications required by this AD shall be done in accordance with Government Aircraft Factories Nomad Alert Service Bulletin AS/B ANMD-27-27, Rev. 1, dated November 5, 1982. 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 AeroSpace Technologies of Australia, Limited, ASTA DEFENCE, Private Bag No. 4, Beach Road Lara 3212, Victoria, Australia. 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 theOffice of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This Amendment supersedes AD 82-25-09, Amendment 39-4510.

(h) This Amendment (39-10004) becomes effective on June 23, 1997.

Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Nomad Models N22S, N22B, and N24A airplanes was published in the Federal Register on December 26, 1996 (61 FR 67965). This action proposed to supersede AD 82-25-09 with a new AD that would retain the repetitive 100 hour time-in-service (TIS) inspections for cracks on the pilot's and co-pilot's control wheel sub-assembly (ASTA part number (P/N) 1/N-45-1208) in the area adjacent to the circumferential weld adjoining the shaft spigot to each control wheel back support plate, modifying any cracked assembly by replacing the assembly with a part of improved design (ASTA P/N 2/N-45-1208 or an FAA approved equivalent part), or re-working the assembly with approved re-worked parts (ASTA P/N 1/N-03-734 or an FAA approved equivalent part), and if there are no signs of cracking during these inspections, terminating the repetitive inspections by accomplishing the modification to the control wheel sub-assemblies with parts of improved design. This modification is considered a terminating action for the repetitive inspections required in AD 82-25-09.

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.

Relevant Service Information
Accomplishment of this action would be in accordance with Government Aircraft Factories (GAF) Nomad Alert Service Bulletin (SB) AS/B ANMD-27-27, Revision 1, dated November 5, 1982.

The FAA's Determination
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 and will not add any additional burden upon the public than was already proposed.

Cost Impact
The FAA estimates that 15 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 6 workhours per airplane to accomplish this action, and that the average labor rate is approximately $60 an hour. Parts cost approximately $1,592 per airplane. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $29,280 or $1,952 per airplane. This figure is based on the cost of the initial inspection and modification and does not account for the repetitive inspections that may occur prior to the proposed modification. The FAA has no way to determine the number of airplanes that may have already accomplished this action.

Regulatory Impact
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 USC 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by removing AD 82-25-09 and by adding a new airworthiness directive (AD) to read as follows: