AD 2012-16-12
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 707-100 Long Body | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-100B Long Body | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-100B Short Body | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-200 | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-300 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-300B Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-300C Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 707-400 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 720 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 720B Series | Airworthiness Directives; The Boeing Company Airplanes |
Unsafe Condition
Cracking of the midspar fittings, which could result in separation of the nacelle strut and engine from the airplane while in flight, and consequent loss of controllability of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a detailed inspection of the midspar fittings of the nacelle strut to confirm the correct part number is installed, and install the correct part number if necessary. Perform repetitive high frequency eddy current (HFEC) inspections of the midspar fittings of the nacelle strut for cracks, and repair if necessary. Perform repetitive general visual inspections of the nacelle struts to verify that the nacelle strut has not drooped below its normal position, apply the droop stripe to the nacelle strut and sailboat fairing if necessary, and perform repair if necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 120 days after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
All The Boeing Company 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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of cracking of the midspar fittings, and of the engine and nacelle strut separating from the airplane. This AD requires performing a detailed inspection of the midspar fittings of the nacelle strut to confirm that the correct part number is installed, and installing the correct part number if necessary; performing repetitive high frequency eddy current (HFEC) inspections of the midspar fittings of the nacelle strut for cracks, and repair if necessary; and performing repetitive general visual inspections of the nacelle struts to verify that the nacelle strut has not drooped below its normal position, applying the droop stripe to the nacelle strut and sailboat fairing if necessary, and performing repair if necessary. We are issuing this AD to detect and correct cracking of the midspar fitting, which could result in separation of the nacelle strut and engine from the airplane while in flight, and consequent loss of controllability of the airplane.
Applicability Source Text
Show captured applicability text from the source AD
(c) Applicability
This AD applies to all The Boeing Company 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.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 77, Number 160 (Friday, August 17, 2012)]
[Rules and Regulations]
[Pages 49708-49710]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-19819]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0490; Directorate Identifier 2012-NM-066-AD;
Amendment 39-17159; AD 2012-16-12]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 707 airplanes, and Model 720 and 720B series
airplanes. This AD was prompted by reports of cracking of the midspar
fittings, and of the engine and nacelle strut separating from the
airplane. This AD requires performing a detailed inspection of the
midspar fittings of the nacelle strut to confirm that the correct part
number is installed, and installing the correct part number if
necessary; performing repetitive high frequency eddy current (HFEC)
inspections of the midspar fittings of the nacelle strut for cracks,
and repair if necessary; and performing repetitive general visual
inspections of the nacelle struts to verify that the nacelle strut has
not drooped below its normal position, applying the droop stripe to the
nacelle strut and sailboat fairing if necessary, and performing repair
if necessary. We are issuing this AD to detect and correct cracking of
the midspar fitting, which could result in separation of the nacelle
strut and engine from the airplane while in flight, and consequent loss
of controllability of the airplane.
DATES: This AD is effective September 21, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 21,
2012.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 (phone: 800-647-5527) is 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: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6577;
fax: (425) 917-6590; email: <a href="/cdn-cgi/l/email-protection#a9ebccdbc1c8c7cc87e8c5c8d3c8dbe9cfc8c887cec6df"><span class="__cf_email__" data-cfemail="bcfed9ced4ddd2d992fdd0ddc6ddcefcdadddd92dbd3ca">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM published in the Federal Register on May 30, 2012 (77 FR
31762). That NPRM proposed to require performing a detailed inspection
of the midspar fittings of the nacelle strut to confirm that the
correct part number is installed, and installing the correct part
number if necessary; performing repetitive HFEC inspections of the
midspar fittings of the nacelle strut for cracks, and repair if
necessary; and performing repetitive general visual inspections of the
nacelle struts to verify that the nacelle strut has not drooped below
its normal position, applying the droop stripe to the nacelle strut and
sailboat fairing if necessary, and performing repair if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received. Boeing and the
National Transportation Safety Board support the NPRM.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 11 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Detailed inspection, repetitive 23 work-hours x $85 per $0 $1,955, per $21,505, per
HFEC inspections, and hour = $1,955, per inspection. inspection.
repetitive general visual inspection.
inspections of the midspar
fittings of the nacelle strut.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspections. We have no
way of determining the number of aircraft that might need these
repairs:
[[Page 49709]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Install the correct part number..... 130 work-hours x $85 per $7,867 x 4 = $31,468....... $42,518
hour = $11,050.
----------------------------------------------------------------------------------------------------------------
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
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-16-12 The Boeing Company: Amendment 39-17159; Docket No. FAA-
2012-0490; Directorate Identifier 2012-NM-066-AD.
(a) Effective Date
This AD is effective September 21, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company 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.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by reports of cracking of the midspar
fittings and of the engine and nacelle strut separating from the
airplane. We are issuing this AD to detect and correct cracking of
the midspar fitting, which could result in separation of the nacelle
strut and engine from the airplane while in flight, and consequent
loss of controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Detailed Inspection
Within 120 days after the effective date of this AD: Do a
detailed inspection of the midspar fittings of engine numbers 2 and
3 nacelle struts to confirm that the correct part number is
installed, in accordance with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012
(which is not incorporated by reference in this AD). If any
incorrect part number is found: Before further flight, install the
correct part number, in accordance with the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012.
Note 1 to paragraph (g) of this AD: Boeing 707 Alert Service
Bulletin A3537, dated January 30, 2012, refers to Boeing 707/720
Service Bulletin 3183, Revision 5, dated September 16, 1993 (which
is not incorporated by reference in this AD), as an additional
source of guidance for high frequency eddy current (HFEC)
inspections of the midspar fittings of engine numbers 2 and 3
nacelle struts for cracks.
(h) HFEC Inspection
At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012, except as provided in paragraph (j) of this AD: Do
an HFEC inspection of the midspar fittings of engine numbers 2 and 3
nacelle struts for cracks, in accordance with the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012, except as provided by paragraph (k) of this AD. If
any crack is found, before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(m) of this AD. Thereafter, repeat the inspection at the applicable
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 707
Alert Service Bulletin A3537, dated January 30, 2012.
(i) General Visual Inspection of the Nacelle Struts of Engine Numbers
1, 2, 3, and 4
At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012, except as provided in paragraph (j) of this AD: Do
a general visual inspection of the nacelle struts of engine numbers
1, 2, 3, and 4 to verify that the nacelle strut has not drooped
below its normal position, in accordance with the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012. Thereafter, repeat the inspection at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012.
(1) If any nacelle strut has drooped below its normal position:
Before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (m) of this AD.
(2) If any nacelle strut has not drooped below its normal
position, and no droop stripe specified in Boeing 707/720 Service
Bulletin 3377, dated November 21, 1979 (which is not incorporated by
reference in this AD) has been applied: At the applicable times in
paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin
A3537, dated January 30, 2012, except as provided
[[Page 49710]]
in paragraph (j) of this AD: Apply the droop stripe to the nacelle
strut and sailboat fairing, on each side of engine numbers 1, 2, 3,
and 4 nacelle struts, in accordance with the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3537, dated
January 30, 2012.
(j) Exception to the Compliance Times
Where Boeing 707 Alert Service Bulletin A3537, dated January 30,
2012, specifies a compliance time based on ``the original issue date
of this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(k) Exception to the Service Information
Where Boeing 707 Alert Service Bulletin A3537, dated January 30,
2012, refers to ``Manual 707, 720 NDT Part 6, 51-00-00 Figure 24 as
an accepted procedure'' for the HFEC inspection, this AD requires
that the inspection be done in accordance with Figure 24, Steel Part
Surface Inspection (Impedance Plane Display), Subject 51-00-00,
Structural-General, of Part 6, Eddy Current, of the Boeing 707/720
Nondestructive Test Manual, Document D6-48023, Revision 120, dated
March 15, 2012.
(l) Credit for Previous Actions
This paragraph provides credit for the installation of the
engine droop lines required by paragraph (i) of this AD, if those
actions were performed before the effective date of this AD using
Boeing 707/720 Service Bulletin 3377, dated November 21, 1979 (which
is not incorporated by reference in this AD).
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#330a1e727d7e1e60565247475f561e72707c1e727e7c701e6156424656404740735552521d545c45"><span class="__cf_email__" data-cfemail="4b72660a050666182e2a3f3f272e660a0804660a06040866192e3a3e2e383f380b2d2a2a652c243d">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
(n) Related Information
(1) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: (425) 917-6577; fax: (425) 917-6590; email:
<a href="/cdn-cgi/l/email-protection#2c6e495e444d4249026d404d564d5e6c4a4d4d024b435a"><span class="__cf_email__" data-cfemail="d092b5a2b8b1beb5fe91bcb1aab1a290b6b1b1feb7bfa6">[email protected]</span></a>.
(2) For service information identified in this AD, that is not
incorporated by reference in this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC
2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing 707 Alert Service Bulletin A3537, dated January 30,
2012.
(ii) Figure 24, Steel Part Surface Inspection (Impedance Plane
Display), Subject 51-00-00, Structural--General, of Part 6, Eddy
Current, of the Boeing 707/720 Nondestructive Test Manual, Document
D6-48023, Revision 120, dated March 15, 2012. The revision level of
this document is identified on only the manual revision Transmittal
Sheet.
(3) For The Boeing Company service information identified in
this AD, contact Boeing Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington
98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680;
Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) You may view this service information at FAA, FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference 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: <a href="http://www.archives.gov/federal-register/cfr/index.html">http://www.archives.gov/federal-register/cfr/index.html</a>.
Issued in Renton, Washington, on August 3, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-19819 Filed 8-16-12; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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