[Federal Register: August 18, 2003 (Volume 68, Number 159)]
[Rules and Regulations]
[Page 49337-49339]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18au03-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-27-AD; Amendment 39-13267; AD 2003-16-14]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Series Airplanes
Equipped with Pratt & Whitney JT9D-3 or JT9D-7 Series Engines (except
JT9D-70 Series Engines)
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to Boeing Model 747 series airplanes equipped with Pratt &
Whitney JT9D-3 or JT9D-7 series engines (except JT9D-70 series
engines), that requires detailed inspections of the upper and lower
surface of the forward lower spar of the nacelle strut for cracking or
other damage, and for any loose or damaged fasteners. This amendment
also requires replacement of loose or damaged fasteners and, if
necessary, associated repair of the forward lower spar. This action is
necessary to detect and correct cracking or other damage to the upper
or lower surface of the forward lower spar and any loose or damaged
fasteners, which could result in reduced structural
[[Page 49338]]
capability of nacelle struts one through four, and possible separation
of a strut and engine from the airplane during flight. This action is
intended to address the identified unsafe condition.
DATES: Effective September 22, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 22, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. 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: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6421; fax (425) 917-6590.
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 Boeing Model 747 series airplanes
equipped with Pratt & Whitney JT9D-3 or JT9D-7 series engines (except
JT9D-70 series engines) was published in the Federal Register on May
29, 2003 (68 FR 31994). That action proposed to require detailed
inspections of the upper and lower surface of the forward lower spar of
the nacelle strut for cracking or other damage, and for any loose or
damaged fasteners. That action also proposed to require replacement of
loose or damaged fasteners and, if necessary, associated repair of the
forward lower spar.
Comments
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, an operator, states that the six-month initial
inspection threshold may require inspections to occur outside of
scheduled heavy maintenance checks, thereby requiring special routing
of airplanes to enable inspections to occur at maintenance facilities
with appropriate equipment and personnel. The commenter further states
that the accomplishment of detailed visual inspections outside of heavy
maintenance checks is not desireable and should be avoided. However,
the commenter acknowledges that the proposed AD appears to provide
sufficient justification for the initial inspection threshold.
From this comment, we infer that the commenter supports the
proposed rule.
Conclusion
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.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 366 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 115 airplanes of U.S. registry
will be affected by this AD, that it will take from 20 to 64 work hours
per airplane to accomplish the required inspections, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be between
$1,300 and $4,160 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 cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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
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. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-16-14 Boeing: Amendment 39-13267. Docket 2002-NM-27-AD.
Applicability: Model 747 series airplanes, equipped with Pratt &
Whitney JT9D-3 or JT9D-7 series engines (excluding JT9D-70 series
engines), as listed in Boeing Alert Service Bulletin 747-54A2209,
dated November 8, 2001; 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
[[Page 49339]]
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 (g) 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, unless accomplished
previously.
To detect and correct cracking or other damage to the structure
of the upper or lower surface of the forward lower spar and any
loose or damaged fasteners, which could result in reduced structural
capability of nacelle struts one through four, and possible
separation of the strut and engine from the airplane during flight,
accomplish the following:
Inspection of Upper Surface of Forward Lower Spar
(a) At the later of the times shown in paragraphs (a)(1) and
(a)(2) of this AD: Perform a detailed inspection of the upper
surface of the forward lower spar to detect cracks, fretting damage,
and any loose or damaged fasteners, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2209, dated November 8, 2001.
(1) Within 500 flight cycles, but no sooner than 300 flight
cycles, after modification of the strut in accordance with AD 95-10-
16, amendment 39-2933; or
(2) Within 6 months after the effective date of this AD.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Inspection of Lower Surface of Forward Lower Spar
(b) If the detailed inspection required by paragraph (a) of this
AD reveals any crack or fretting damage, or any loose or damaged
fastener: Prior to further flight, perform a detailed inspection of
the lower surface of the forward lower spar to detect cracks,
fretting damage, and any loose or damaged fasteners, in accordance
with Part 2 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2209, dated November 8, 2001.
Follow-up Inspection
(c) If the detailed inspection of the upper surface of the
forward lower spar required by paragraph (a) of this AD reveals no
crack or fretting damage and no loose or damaged fastener: At the
later of the times specified in paragraphs (c)(1) and (c)(2) of this
AD, repeat the detailed inspection of the upper surface of the
forward lower spar and perform a detailed inspection of the lower
surface of the forward lower spar, in accordance with Parts 1 and 2,
respectively, of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2209, dated November 8, 2001.
(1) Within 1,500 flight cycles, but no sooner than 1,300 flight
cycles, after modification of the strut, in accordance with AD 95-
10-16; or
(2) Within 18 months after the effective date of this AD.
Optional Follow-up Inspection
(d) If the detailed inspection of the upper surface of the
forward lower spar required by paragraph (a) of this AD reveals no
crack or fretting damage, and no loose or damaged fastener: Prior to
further flight, the operator may elect to perform a detailed
inspection of the lower surface of the forward lower spar to detect
cracks, fretting damage, and any loose or damaged fasteners, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-54A2209, dated November 8, 2001, provided
that the airplane has accumulated at least 1,300 flight cycles since
modification of the strut per AD 95-10-16.
Corrective Action
(e) If any detailed inspection described in paragraph (a), (b),
(c), or (d) of this AD reveals any crack or fretting damage to the
upper or lower surface of the forward lower spar or any loose or
damaged fastener: Prior to further flight, accomplish the actions
specified in paragraph (e)(1) or (e)(2) of this AD, as applicable.
(1) If the crack or fretting damage to the upper or lower
surface of the forward lower spar falls within the parameters
specified in Figure 4 or 5 (as applicable) of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2209, dated
November 8, 2001, and the airplane has accumulated 1,300 flight
cycles or more since modification of the strut per AD 95-10-16:
Remove any loose or damaged fasteners, repair any cracks or fretting
damage to the upper or lower surface of the forward lower spar, and
install new fasteners, in accordance with the Accomplishment
Instructions of the service bulletin. No further action is required
by this AD.
(2) If the crack or fretting damage to the upper or lower
surface of the forward lower spar does not fall within the
parameters specified in Figure 4 or 5 (as applicable) of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2209, dated November 8, 2001, or if the airplane has accumulated
fewer than 1,300 flight cycles since modification of the strut per
AD 95-10-16: Accomplish additional repair per a method approved by
the Manager, Seattle Aircraft Certification Office (ACO), FAA, or
per data meeting the type certification basis of the airplane
approved by a Boeing Company Designated Engineering Representative
who has been authorized by the Manager, Seattle ACO, to make such
findings. For a repair method to be approved as required by this
paragraph, the approval must specifically reference this AD.
(f) If the detailed inspection specified in paragraph (c) or (d)
of this AD reveals no cracks or other damage to the upper or lower
surface of the forward lower spar and no loose or damaged fasteners,
no further action is required by this AD.
Alternative Methods of Compliance
(g) 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, Seattle ACO, FAA. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Seattle ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(h) 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.
Incorporation by Reference
(i) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 747-54A2209,
dated November 8, 2001. 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 Boeing
Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-
2207. 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.
Effective Date
(j) This amendment becomes effective on September 22, 2003.
Issued in Renton, Washington, on August 6, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-20712 Filed 8-15-03; 8:45 am]
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