[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
