
[Federal Register: March 18, 2008 (Volume 73, Number 53)]
[Rules and Regulations]               
[Page 14378-14381]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18mr08-5]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0216; Directorate Identifier 2007-NM-122-AD; 
Amendment 39-15435; AD 2008-06-23]
RIN 2120-AA64

 
Airworthiness Directives; McDonnell Douglas Model DC-8-55, DC-8F-
54, and DC-8F-55 Airplanes; and Model DC-8-60, DC-8-70, DC-8-60F, and 
DC-8-70F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain McDonnell Douglas Model DC-8-55, DC-8F-54, 
and DC-8F-55 airplanes; and Model DC-8-60, DC-8-70, DC-8-60F, and DC-8-
70F series airplanes. The existing AD currently requires a one-time 
inspection for previous repairs of the aft fuselage skin panel at the 
longeron 28 skin splice, repetitive inspections for cracks of the same 
area, and related investigative and corrective actions. The existing AD 
also provides optional actions for extending the repetitive inspection 
intervals. This new AD re-defines and more clearly describes the 
optional actions for extending the repetitive inspection intervals. 
This AD results from our determination that the inspections and actions 
described in the existing AD do not adequately address the unsafe 
condition. We are issuing this AD to detect and correct cracks in the 
aft fuselage skin at the longeron 28 skin splice, which could lead to 
loss of structural integrity of the aft fuselage, resulting in rapid 
decompression of the airplane.

DATES: This AD becomes effective April 22, 2008.
    The incorporation by reference of certain publications listed in 
the AD was approved previously by the Director

[[Page 14379]]

of the Federal Register as of February 28, 2007 (72 FR 3044, January 
24, 2007).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5322; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2007-02-02, amendment 
39-14889 (72 FR 3044, January 24, 2007). The existing AD applies to 
certain McDonnell Douglas Model DC-8-55, DC-8F-54, and DC-8F-55 
airplanes; and Model DC-8-60, DC-8-70, DC-8-60F, and DC-8-70F series 
airplanes. That NPRM was published in the Federal Register on November 
21, 2007 (72 FR 65471). That NPRM proposed to continue to require a 
one-time inspection for previous repairs of the aft fuselage skin panel 
at the longeron 28 skin splice, repetitive inspections for cracking of 
the same area, and related investigative and corrective actions. That 
NPRM also proposed to re-define and more clearly describe the optional 
actions for extending the repetitive inspection intervals.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that was 
received on the NPRM.

Request To Give Credit for Prior Submission of Inspection Findings

    UPS agrees with the intent of the NPRM. UPS requests, however, that 
we revise paragraphs (k)(1) and (k)(2) of the NPRM to specify 
submitting positive findings ``unless previously submitted to Boeing 
for compliance with AD 2007-02-02.'' UPS asserts that this would allow 
all alternative methods of compliance (AMOCs) that apply to AD 2007-02-
02 to be applicable to this new AD ``as per paragraph (k)(4) [sic].'' 
UPS states that this will prevent operators from having to submit data 
already submitted previously for AD 2007-02-02, and again requesting 
AMOC approval.
    We do not agree with this request. Operators are always given 
credit for work previously performed according to the existing AD by 
means of the phrase in the compliance paragraph of this AD that states, 
``Required * * * unless the actions have already been done.'' In 
addition, paragraph (l)(4) of this AD (rather than paragraph (k)(4) as 
specified by the commenter) states that AMOCs approved for compliance 
with AD 2007-02-02 are acceptable for compliance with the corresponding 
provisions of this AD. For these reasons, no change is needed to the AD 
in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD as proposed.

Costs of Compliance

    There are approximately 508 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 244 airplanes of U.S. registry 
are affected by this AD. The average labor rate is $80 per work hour. 
This AD adds no additional costs; however, we are repeating the costs 
from AD 2007-02-02 for the convenience of affected operators.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                    Work hours       Cost per airplane                Fleet cost
----------------------------------------------------------------------------------------------------------------
Initial inspection for doubler    2 to 4.............  $160 to $320.......  $39,040 to $78,080.
 installation.
Repetitive inspections (per       2 to 8.............  $160 to $640.......  $39,040 to $156,160.
 inspection cycle).
Repair..........................  164 to 184.........  $13,120 to $14,720.  $3,201,280 to $3,591,680.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

[[Page 14380]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14889 (72 FR 3044, January 24, 2007) and by 
adding the following new airworthiness directive (AD):

2008-06-23 McDonnell Douglas: Amendment 39-15435. Docket No. FAA-
2007-0216; Directorate Identifier 2007-NM-122-AD.

Effective Date

    (a) This AD becomes effective April 22, 2008.

Affected ADs

    (b) This AD supersedes AD 2007-02-02.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-55, DC-8F-
54, DC-8F-55, DC-8-61, DC-8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-
63F, DC-8-71, DC-8-72, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin DC8-53A080, dated June 22, 2004.

Unsafe Condition

    (d) This AD results from our determination that the inspections 
and actions described in the existing AD do not adequately address 
the unsafe condition. We are issuing this AD to detect and correct 
cracks in the aft fuselage skin at the longeron 28 skin splice, 
which could lead to loss of structural integrity of the aft 
fuselage, resulting in rapid decompression of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2007-02-02

One-Time Inspection for Previous Repairs

    (f) For all airplanes: At the applicable time in paragraph 
(f)(1) or (f)(2) of this AD, do a general visual inspection to 
determine if there are previous repairs of the aft fuselage skin 
panel at the longeron 28 skin splice; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
53A080, dated June 22, 2004. Then do the applicable actions 
specified in paragraphs (g) and (h) of this AD.
    (1) For airplanes that have accumulated fewer than 24,000 total 
flight cycles as of February 28, 2007 (the effective date of AD 
2007-02-02): Within 24 months after February 28, 2007, or prior to 
accumulating 24,000 total flight cycles, whichever occurs later.
    (2) For airplanes that have accumulated 24,000 total flight 
cycles or more as of February 28, 2007: Within 12 months after 
February 28, 2007.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Repetitive Inspections for Areas That Do Not Have a Previous Repair

    (g) For areas that do not have a previous repair: Before further 
flight after the initial inspection in paragraph (f) of this AD, do 
general visual and high-frequency eddy current (HFEC) inspections 
for discrepancies at longeron 28 between the bolted connection of 
the tail section to forward of the flat aft pressure bulkhead, on 
both the left and right sides, and do all applicable related 
investigative and corrective actions before further flight. Do all 
actions in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin DC8-53A080, dated June 22, 2004. Repeat the 
general visual and HFEC inspections thereafter at intervals not to 
exceed 2,000 flight cycles until an optional action in paragraph (i) 
of this AD is accomplished.

Repetitive Inspections and Repair for Areas That Have a Previous Repair

    (h) For areas that have a previous repair: Within 24 months 
after accomplishing the initial inspection in paragraph (f) of this 
AD, remove the previous repair(s), and install a local repair, in 
accordance with Boeing DC-8 Service Rework Drawing SR08530032, dated 
January 13, 2004, including Boeing Parts List PL SR08530032, dated 
January 7, 2004, Boeing Advance Engineering Order, Advanced Drawing 
Change A, dated April 1, 2004, and Boeing Engineering Order, dated 
January 13, 2004. Do the inspections in paragraph (j) of this AD 
thereafter at the applicable interval specified in paragraph (j)(1) 
or (j)(2) of this AD.

New Requirements of This AD

Optional Modification/Repair

    (i) Installing a full-length preventive modification, doing a 
full-length repair, or doing a local repair, in accordance with 
Boeing DC-8 Service Rework Drawing SR08530032, dated January 13, 
2004, including Boeing Parts List PL SR08530032, dated January 7, 
2004; Boeing Advance Engineering Order, Advanced Drawing Change A, 
dated April 1, 2004; and Boeing Engineering Order, dated January 13, 
2004; ends the repetitive inspection intervals specified in 
paragraph (g) of this AD.

Extended Repetitive Inspection Intervals

    (j) After removing the previous repair(s) and doing the actions 
specified in paragraph (h) of this AD or doing any optional repair 
or modification described in paragraph (i) of this AD: Do the 
actions described in paragraph (j)(1) or (j)(2) of this AD as 
applicable, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin DC8-53A080, dated June 22, 2004. If 
any discrepancy is discovered during any inspection required by this 
paragraph, before further flight, repair the discrepancy using a 
method approved in accordance with the procedures specified in 
paragraph (l) of this AD.
    (1) For areas that have been repaired on airplanes that do have 
internal finger doublers installed: Within 30,000 flight cycles 
after doing the optional repair or modification, do a general visual 
inspection for discrepancies along all four external edges of the 
doublers. Repeat the inspection thereafter at intervals not to 
exceed 5,000 flight cycles.
    (2) For areas that have been repaired on airplanes that do not 
have internal finger doublers installed: Do the actions specified in 
paragraph (j)(2)(i) or (j)(2)(ii) of this AD, as applicable.
    (i) For any repair that is 12 inches or less along the longeron: 
Within 15,000 flight cycles after removing the previous repair(s) 
and doing the actions specified in paragraph (h) of this AD or doing 
any optional repair or modification specified in paragraph (i) of 
this AD, do a general visual inspection for discrepancies along all 
four external edges of the doublers. Repeat the general visual 
inspection thereafter at intervals not to exceed 5,000 flight 
cycles.
    (ii) For any repair that is greater than 12 inches in length 
along the longeron: Within 15,000 flight cycles after removing the 
previous repair(s) and doing the actions specified in paragraph (h) 
of this AD or doing any optional repair or modification specified in 
paragraph (i) of this AD, do a low-frequency eddy current (LFEC) 
inspection for discrepancies along all four external edges of the 
doublers. Repeat the LFEC inspection thereafter at intervals not to 
exceed 10,000 flight cycles.

Reporting of Results

    (k) Submit a report of positive findings of the inspections 
required by paragraphs (g) and (j) of this AD to Boeing Commercial 
Airplanes, Manager, Structure/Payloads, Technical and Fleet Support, 
Service Engineering/Commercial Aviation Services, Long Beach 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, at 
the applicable time specified in paragraph (k)(1) or (k)(2) of this 
AD. The report must include the inspection results, a description of 
any discrepancies found, the airplane

[[Page 14381]]

fuselage number, and the total number of landings and flight hours 
on the airplane. Information collection requirements contained in 
this AD have been approved by the Office of Management and Budget 
(OMB) under the provisions of the Paperwork Reduction Act (44 U.S.C. 
3501 et seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For any inspection accomplished after the effective date of 
this AD: Submit the report within 30 days after performing the 
inspection.
    (2) For any inspection accomplished prior to the effective date 
of this AD: Submit the report within 30 days after the effective 
date of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, the repair must meet the certification 
basis of the airplane and 14 CFR 25.571, Amendment 45, and the 
approval must specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2007-02-02, 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (m) You must use Boeing Alert Service Bulletin DC8-53A080, dated 
June 22, 2004; and Boeing DC-8 Service Rework Drawing SR08530032, 
dated January 13, 2004, including Boeing Parts List PL SR08530032, 
dated January 7, 2004, Boeing Advance Engineering Order, Advanced 
Drawing Change A, dated April 1, 2004, and Boeing Engineering Order, 
dated January 13, 2004; as applicable, to perform the actions that 
are required by this AD, unless the AD specifies otherwise.
    (1) On February 28, 2007 (72 FR 3044, January 24, 2007), the 
Director of the Federal Register approved the incorporation by 
reference of these documents.
    (2) Contact Boeing Commercial Airplanes, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of 
this service information. You may review copies at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 9, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-5295 Filed 3-17-08; 8:45 am]

BILLING CODE 4910-13-P
