### 58213 Federal Register / Vol. 60, No. 227 / Monday, November 27, 1995 / Rules and Regulations

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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from 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), 40101, 40113,
44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness
directive:

95–24–01 McDonnell Douglas: Amendment
39–9433. Docket 95–NM–50–AD. Applicability: Model DC–10–10 series airplanes, as listed in McDonnell Douglas DC–10 Service Bulletin 57–36, Revision 7, dated December 11, 1992, certificated in any category.

Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 use the authority provided in paragraph (c) 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 airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

Note 2: Inspections and modifications required by paragraphs (g) and (h) of AD 94– 23–01, amendment 39–9063, accomplished prior to the effective date of this amendment in accordance with McDonnell Douglas DC– 10 Service Bulletin 57–123, dated June 8, 1993, or McDonnell Douglas DC–10 Service Bulletin 57–36, Revision 6, dated February 25, 1991, are considered acceptable for compliance with the applicable inspections and modifications required by this
amendment for the affected structure.

To prevent fatigue-related cracking, which could lead to the failure of the aft spar cap and subsequent reduced structural integrity of the wing, accomplish the following:

(a) Prior to the accumulation of 15,000 total landings or within 2,000 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection of the wings to detect cracks in the aft spar lower cap, in the stringer butterfly clips on
the bulkheads at stations X

ors=372.000 and

X

ors=402.000, and in the fastener holes of the access doors of the inboard upper surface, in accordance with McDonnell Douglas DC–10 Service Bulletin 57–36, Revision 7, dated December 11, 1992.

(1) If no cracks are detected, repeat the inspection thereafter at intervals not to exceed 2,000 landings until the modification required by paragraph (b) of this AD is accomplished.

(2) If any crack is detected, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

(b) Prior to the accumulation of 42,000 total landings or within 5 years after the effective date of this AD, whichever occurs later, modify the aft spar lower cap, the stringer butterfly clips on the bulkheads at

stations X

ors=372.000 and X

ors=402.000, and
the fastener holes of the access doors of the inboard upper surface of the wings, in accordance with McDonnell Douglas DC–10 Service Bulletin 57–36, Revision 7, dated December 11, 1992. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirement of
this AD.

(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may
add comments and then send it to the Manager, Los Angeles ACO.

Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (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) The inspections, repair, and
modification shall be done in accordance with McDonnell Douglas DC–10 Service Bulletin 57–36, Revision 7, dated December 11, 1992. 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department C1– L51 (2–60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on December 27, 1995.

Issued in Renton, Washington, on November 9, 1995.

S.R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95–28797 Filed 11–24–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–04–AD; Amendment 39–9436; AD 95–24–04]

Airworthiness Directives; Airbus Model A300 and A300–600 Series Airplanes

AGENCY : Federal Aviation Administration, DOT.

ACTION : Final rule.

SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300–600 series airplanes, that requires repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. This amendment is prompted by reports indicating that cracks have been found in the rear spar web of thewings between ribs 1 and 2 of an inservice airplane and during testing on the fatigue test wing; the cracking occurred due to fatigue-related high shear stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the wing.

DATES : Effective December 27, 1995.

The incorporation by reference of certain publications listed in the

### 58214 Federal Register / Vol. 60, No. 227 / Monday, November 27, 1995 / Rules and Regulations

regulations is approved by the Director of the Federal Register as of December 27, 1995.

ADDRESSES : The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be
examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Phil Forde, Aerospace Engineer, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (206) 227–2146; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to all Airbus Model A300 and A300–600 series airplanes was published in the Federal Register on May 4, 1995 (60 FR 22011). That action proposed to require repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received.

The commenter supports the proposed rule.

After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 89 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $16,020, or $180 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.

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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from 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), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness
directive:

95–24–04 Airbus Industrie: Amendment 39–
9436. Docket 95–NM–04–AD. Applicability: All Model A300 and Model A300–600 series airplanes, 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 use the authority provided in paragraph (f) 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 airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue-related cracking in the rear spar web of the wings, which could result in reduced structural integrity of the wing, accomplish the following:

(a) For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.

(b) For Model A300 B4–103, and B4–2C series airplanes: Prior to the accumulation of 19,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles.

(c) For Model A300 B4–200 series airplanes: Prior to the accumulation of 17,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.

(d) For Model A300–600 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, and F4–605R series airplanes: Prior to the accumulation of 21,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.

(e) If any crack is detected during any inspection required by this AD, prior to further flight, repair the crack in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994, or Airbus Service Bulletin A300–57–6059, dated August 12, 1994, as applicable; or in accordance with a method approved by the Manager, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate.

(f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM–113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then

### 58215 Federal Register / Vol. 60, No. 227 / Monday, November 27, 1995 / Rules and Regulations

send it to the Manager, Standardization Branch, ANM–113.

Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch,
ANM–113.

(g) 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.

(h) The inspections and repairs shall be
done in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994, or Airbus Service Bulletin A300–57– 6059, dated August 12, 1994, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.

(i) This amendment becomes effective on December 27, 1995.

Issued in Renton, Washington, on November 9, 1995.
S. R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95–28798 Filed 11–24–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–114–AD; Amendment 39–9427; AD 95–23–07]

Airworthiness Directives; McDonnell Douglas Model MD–11 Series Airplanes

AGENCY : Federal Aviation Administration, DOT.

ACTION : Final rule.

SUMMARY : This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD–11 series airplanes, that currently requires visual inspections to detect cracking of the
outboard and inboard surfaces of the upper spar angles of the wing pylons, and repair of any cracked upper spar angles. This amendment requires eddy current inspections to detect cracking of the upper spar angles on the left and right sides of the wing pylons, and replacement of the spar angles as terminating action for the inspections. This amendment is prompted by the development of a modification that positively addresses the unsafe condition. The actions specified by this AD are intended to prevent loss of loadcarrying and fail-safe capability of the upper inboard spar cap of the wing pylon, which could subsequently reduce the structural integrity of the airplane.

DATES : Effective December 27, 1995.

The incorporation by reference of certain publications, as listed in the regulations, is approved by the Director
of the Federal Register as of December 27, 1995.

The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11–54A049 R01, Revision 1, dated February 7, 1995, listed in the regulations, was approved previously by
the Director of the Federal Register as of March 17, 1995 (60 FR 11623, March 2, 1995).

ADDRESSES : The service information referenced in this AD may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department C1–L51 (2–60). This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT : Wahib Mina, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (310) 627– 5324; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 95–04–15, amendment 39–9167 (60 FR 11623, March 2, 1995), which is applicable to certain McDonnell Douglas Model MD– 11 series airplanes, was published in the Federal Register on August 21, 1995 (60 FR 43415). The action proposed to continue to require visual inspections to detect cracking of the outboard and inboard surfaces of the upper spar angles on the number 1 and number 3 wing pylons. However, the action also proposed to require eddy current inspections to detect cracking on the forward end of the left and right sides of the upper spar angles on the number 1 and number 3 wing pylons, and replacement of the upper spar angles on the left and right sides of the number 1 and number 3 wing pylons. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the two
comments received.

Both commenters support the proposed rule.

After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

There are approximately 123 Model MD–11 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 47 airplanes of U.S. registry will be affected by this AD.

The visual inspections that are currently required by AD 95–04–15 and
retained in this new AD take approximately 10 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact on U.S. operators of the actions currently required is estimated to be $28,200, or $600 per airplane, per inspection.

The eddy current inspections that are required by this new AD will take approximately 10 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact on U.S. operators of the new requirements of this AD is estimated to be $28,200, or $600 per airplane.

The new requirement to replace the spar angle that is required in this AD action will take approximately 440 work hours to accomplish the replacement of one spar angle per wing pylon (with two wing pylons per airplane), or 550 work hours to accomplish the replacement of two spar angles per wing pylon (with two wing pylons per airplane), at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact on U.S. operators of the replacement requirement is estimated to be $26,400 to replace one spar angle per wing pylon (or $52,800 per airplane), or $33,000 to replace two spar angles per wing pylon (or $66,000 per airplane).

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.

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