[Federal Register: October 16, 2007 (Volume 72, Number 199)]
[Rules and Regulations]
[Page 58495-58497]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16oc07-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28811; Directorate Identifier 2006-NM-246-AD;
Amendment 39-15233; AD 2007-21-15]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 707 Airplanes and Model
720 and 720B Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Boeing Model 707 airplanes and Model 720 and 720B series airplanes.
This AD requires identifying the material used in the elevator hinge
support fittings of the horizontal stabilizer trailing edge, doing
repetitive detailed inspections for cracking of the fittings and
corrective actions if necessary, and doing an eventual terminating
action. This AD results from a report that stress corrosion cracking of
the elevator hinge support fittings has been discovered on several
Model 707 airplanes. We are issuing this AD to prevent cracking of the
elevator hinge support fittings, which could reduce the elevator
support stiffness and lead to in-flight airframe vibration, consequent
damage to the elevator and horizontal stabilizer, and reduced
controllability of the airplane.
DATES: This AD becomes effective November 20, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 20,
2007.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
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: Duong Tran, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6452; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to all Boeing Model 707
airplanes and Model 720 and 720B series airplanes. That NPRM was
published in the Federal Register on July 30, 2007 (72 FR 41462). That
NPRM proposed to require identifying the material used in the elevator
hinge support fittings of the horizontal stabilizer trailing edge,
doing repetitive detailed inspections for cracking of the fittings and
corrective actions if necessary, and doing an eventual terminating
action.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Clarification of Costs of Compliance
In the NPRM, the estimated cost per airplane for the proposed
detailed inspections was correct, but the fleet cost was erroneously
calculated to be $47,840 per inspection cycle. We have
[[Page 58496]]
corrected that amount to $99,840 per inspections cycle.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously. We have determined that this change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Costs of Compliance
There are about 185 airplanes of the affected design in the
worldwide fleet. This AD affects about 52 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD, at an average labor rate of $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Work hours Parts Cost per Airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Material verification........... 1................. No parts needed... $80............... $4,160.
Detailed inspections............ 24, per inspection No parts needed... $1,920............ $99,840, per
cycle. inspection cycle.
Modification (fabrication and 6................. Operator supplied. $480.............. $24,960.
installation of nutplates).
Terminating action.............. 132............... $53,078 \1\ or $63,638 \1\ or Up to $5,112,120.
$87,750 \2\. $98,310 \2\.
----------------------------------------------------------------------------------------------------------------
\1\ for Group 1 airplanes.
\2\ for Group 2 airplanes.
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.
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
adding the following new airworthiness directive (AD):
2007-21-15 Boeing: Amendment 39-15233. Docket No. FAA-2007-28811;
Directorate Identifier 2006-NM-246-AD.
Effective Date
(a) This AD becomes effective November 20, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Model 707-100 long body, -200, -100B
long body, and -100B short body series airplanes; Model 707-300, -
300B, -300C, and -400 series airplanes; and Model 720 and 720B
series airplanes; certificated in any category.
Unsafe Condition
(d) This AD results from a report that stress corrosion cracking
of the elevator hinge support fittings of the horizontal stabilizer
trailing edge has been discovered on several Model 707 airplanes. We
are issuing this AD to prevent cracking of the elevator hinge
support fittings, which could reduce the elevator support stiffness
and lead to in-flight airframe vibration, consequent damage to the
elevator and horizontal stabilizer, and reduced controllability 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.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3518, dated October 9, 2006.
Material Identification
(g) Within 180 days after the effective date of this AD or
before further flight after any horizontal stabilizer is replaced:
Verify the type of material used in the elevator hinge support
fittings of the horizontal stabilizer trailing edge, in accordance
with Part 1 of the Accomplishment Instructions of the service
bulletin, then do the requirements of paragraph (g)(1) or (g)(2) of
this AD, as applicable. Repeat the verification before further
flight after the replacement of any hinge support fitting.
(1) For any hinge support fitting made of 7075-T7351 material:
No further action is required by paragraph (h) or (i) of this AD.
(2) For any hinge support fitting made of 7079-T6 or 7075-T6
material: Do the actions required by paragraph (h) of this AD.
[[Page 58497]]
Repetitive Inspections, One-time Modification, and Corrective Actions
(h) Before further flight after doing paragraph (g) of this AD,
do a detailed inspection for cracking of the hinge support fittings
and modify certain segments of the rib webs, in accordance with Part
2 of the Accomplishment Instructions of the service bulletin. For
any hinge support fitting found to be cracked or damaged, before
further flight, do the actions required by paragraph (h)(1) or
(h)(2) of this AD; in accordance with Part 3 of the Accomplishment
Instructions of the service bulletin. Do all actions in accordance
with the Accomplishment Instructions of the service bulletin; except
where the service bulletin specifies to contact the manufacturer for
repair procedures, this AD requires repair using a method approved
in accordance with the procedures specified in paragraph (k) of this
AD.
(1) Replace the fitting with a serviceable fitting made of 7079-
T6 or 7075-T6 material. Repeat the detailed inspection thereafter at
intervals not to exceed 180 days, until the terminating action
required by paragraph (i) of this AD has been done.
(2) Replace the fitting with a new, improved fitting made of
7075-T7351 material.
Terminating Action
(i) For all airplanes: Within 48 months after the effective date
of this AD, replace all hinge support fittings made of 7079-T6 or
7075-T6 material with new, improved fittings made of 7075-T7351
material, in accordance with Part 4 of the Accomplishment
Instructions of the service bulletin. Doing this action terminates
all requirements of paragraphs (g) and (h) of this AD.
Parts Installation
(j) As of the effective date of this AD, no person may install,
on any airplane, a new or serviceable hinge support fitting made of
7079-T6 or 7075-T6 material, unless the requirements of paragraph
(h)(1) of this AD are accomplished.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle 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, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane and the approval must specifically refer to this AD.
Material Incorporated by Reference
(l) You must use Boeing 707 Alert Service Bulletin A3518, dated
October 9, 2006, to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207,
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 October 5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-20219 Filed 10-15-07; 8:45 am]
BILLING CODE 4910-13-P