[Federal Register Volume 60, Number 141 (Monday, July 24, 1995)]
[Rules and Regulations]
[Pages 37813-37816]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17552]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-185-AD; Amendment 39-9312; AD 95-15-09]


Airworthiness Directives; British Aerospace Model BAC 1-11-200 
and -400 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain British Aerospace Model BAC 1-11-200 and -400 
series airplanes, that requires various inspections to detect 
discrepancies of fuselage frames at certain stations, and correction of 
discrepancies; and rework to limit the maximum differential operating 
pressure of the fuselage. This amendment will also require eventual 
modification of fuselage frames at certain stations, which will 
terminate the repetitive inspection requirements. This amendment is 
prompted by reports of fatigue cracking in certain fuselage frames in 
the vicinity of the passenger door at floor level due to fatigue-
related stress. The actions specified by this AD are intended to detect 
and prevent such fatigue-related cracking, which could result in 
reduced structural integrity of the fuselage pressure vessel and 
possible decompression of the pressurized cabin.

DATES: Effective August 23, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 23, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol 
BS99 7AR, England. 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: William Schroeder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2148; 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 certain British Aerospace Model 
BAC 1-11-200 and -400 series airplanes was published in the Federal 
Register on April 17, 1995 (60 FR 19175). That action proposed to 
require various repetitive inspections to detect structural 
discrepancies of the various structural configurations of the fuselage 
frames at stations 178 and 213.5, and correction of any discrepancy. 
That action also proposed to require rework to limit the maximum 
differential operating pressure of the fuselage. Additionally, that 
action proposed to require eventual modification of fuselage frames at 
stations 178 and 213.5, which would constitute terminating action for 
the repetitive inspection requirements.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 


[[Page 37814]]
to the proposal or the FAA's determination of the cost to the public. 
The FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed.
    The FAA estimates that 31 airplanes of U.S. registry would be 
affected by this proposed AD.
    It will take approximately 8 work hours per airplane to accomplish 
the required inspection at an average labor rate of $60 per work hour. 
Based on these figures, the total cost impact of the inspection 
required by this AD on U.S. operators is estimated to be $14,880, or 
$480 per airplane, per inspection.
    It will take approximately 80 work hours per airplane to accomplish 
the required modification at an average labor rate of $60 per work 
hour. Required parts will cost approximately $2,000 per airplane. Based 
on these figures, the total cost impact of the modification required by 
this AD on U.S. operators is estimated to be $210,800, or $6,800 per 
airplane.
    The total 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 
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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

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

95-15-09 British Aerospace Airbus Limited (Formerly British 
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft 
Group): Amendment 39-9312. Docket 94-NM-185-AD.

    Applicability: Model BAC 1-11-200 and -400 series airplanes on 
which British Aerospace Modifications PM5445 and PM5713 have not 
been installed, 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 (h) 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 detect and prevent fatigue-related cracking in fuselage 
frames at stations 178 and 213.5 in the vicinity of the passenger 
door at floor level, which could result in reduced structural 
integrity of the fuselage pressure vessel and possible decompression 
of the pressurized, accomplish the following:
    (a) For airplanes unrepaired or not reinforced by repair on 
frames 178 and 213.5, in the area between stringers 25L and 27L: 
Accomplish paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD, 
in accordance with British Aerospace Airbus Limited Alert Service 
Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.1 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.1 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (a)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.1 of the Accomplishment 
Instructions of the alert service bulletin.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.1.5 or 2.1.10, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frame at stations 178 
and 213.5 in accordance with paragraph 2.1.5 or 2.1.10, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (a)(1) and 
(a)(2) this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 pounds per 
square inch (psi), in accordance with the alert service bulletin.
    (b) For airplanes on which Structural Repair Manual, figure 76, 
repair in-situ has been accomplished: Accomplish paragraphs (b)(1), 
(b)(2), (b)(3), and (b)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.2 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.2 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (b)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.2 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.2.6 or 2.2.9, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frame at stations 178 
and 213.5 in accordance with paragraph 2.2.6 or 2.2.9, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (b)(1) and 
(b)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 

[[Page 37815]]
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (c) For airplanes on which Structural Repair Manual, figure 87, 
repair has been accomplished: Accomplish paragraphs (c)(1), (c)(2), 
(c)(3), and (c)(4) of this AD, in accordance with British Aerospace 
Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated 
January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.3 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.3 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (c)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.3 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.3.5 or 2.3.8, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.3.5 or 2.3.8, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (c)(1) and 
(c)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (d) For airplanes on which Structural Repair Manual, figure 110 
or 111, repair has been accomplished: Accomplish paragraphs (d)(1), 
(d)(2), (d)(3), and (d)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.4 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.4 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (d)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.4.5 or 2.4.8, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.4.5 or 2.4.8, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (d)(1) and 
(d)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (e) For airplanes on which Structural Repair Manual, figure 76, 
reinforcement has been accomplished: Accomplish paragraphs (e)(1), 
(e)(2), (e)(3), (e)(4), and (e)(5) of this AD, in accordance with 
British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, 
Issue 1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.5 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.5 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (e)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.5 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.5.5 or 2.5.10, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.5.5 or 2.5.10, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (e)(1) and 
(e)(2) of this AD.
    (4) For airplanes operated at a cabin maximum pressure 
differential in excess of 7.5 psi, prior to the threshold times 
specified in Table C of the service bulletin, replace the 
reinforcements accomplished in accordance with the Structural Repair 
Manual, figure 76, with reinforcements accomplished in accordance 
with Structural Repair Manual 53-02-00, figure 110 or 111, as 
specified in the alert service bulletin.
    (5) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (f) For airplanes on which Structural Repair Manual, figure 87, 
reinforcement has been accomplished: Accomplish paragraphs (f)(1), 
(f)(2), (f)(3), and (f)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.6 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.6 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (f)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.6 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.6.6 or 2.6.9, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.6.6 or 2.6.9, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (f)(1) and 
(f)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (g) For airplanes on which repairs other than those described in 
the Structural Repair Manual have been accomplished on frames 178 
and 213.5, in the area between stringers 25L and 27L: Accomplish 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (1) Within 6 months after the effective date of this AD, submit 
the following for approval to the Manager, Standardization Branch, 
ANM-113, FAA, Transport Airplane Directorate:
    (i) Procedures and schedule for accomplishing the initial and 
repetitive inspections of the fuselage frames at stations 178 and 
213.5; and
    (ii) Schedule for installation of Modification PM5993 or 
Structural Repair Manual, figure 110 and 111, as applicable, at the 
fuselage frames at stations 178 and 213.5.
    (2) Within 6 months after the procedures and schedules are 
approved, revise the FAA-approved maintenance program to include 
these procedures.
    (3) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 

[[Page 37816]]
accordance with British Aerospace Airbus Limited Alert Service Bulletin 
53-A-PM5993, Issue 1, dated January 11, 1993.
    (h) 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, 
FAA, Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then 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.

    (i) 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.
    (j) The actions shall be done in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993. 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 
British Aerospace, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, 
England. 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.
    (k) This amendment becomes effective on August 23, 1995.

    Issued in Renton, Washington, on July 12, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-17552 Filed 7-21-95; 8:45 am]
BILLING CODE 4910-13-U