### 21422 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations

dated November 15, 2011. The kit (P/N SB680–24–11) contains 2 sleeves, 4 splices, 2 diodes (P/N 1N4006), and instructions.

(h) Revise Airplane Flight Manual (AFM)

Before further flight after accomplishing the actions required by paragraph (g) of this AD, do the applicable actions specified in paragraph (h)(1) or (h)(2) of this AD.

(1) For airplanes using Cessna 680 Citation Sovereign AFM, Revision 9, dated May 24,
2010: Revise the Cessna 680 Citation Sovereign AFM to include the information in Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC–R09–13, dated October 15, 2010, and remove the temporary changes (TCs) identified in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–13, dated October 15, 2010, introduces procedures to use when the left or right generator is selected OFF. Operate the airplane according to the procedures in Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC–R09–13, dated October 15, 2010.

(i) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–09, dated October 15, 2010.

(ii) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–10, dated October 15, 2010.

(iii) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–11, dated October 15, 2010.

(iv) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–12, dated October 15, 2010.

Note 1 to paragraph (h)(1) of this AD: Updating Cessna 680 Citation Sovereign AFM, Revision 9, dated May 24, 2010, may be done by inserting a copy of Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC–R09–13, dated October 15, 2010, into the AFM. Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC–R09–13, dated October 15, 2010, should be removed and discarded when Revision 10, dated June 30, 2011, has been collated into the basic airplane flight manual.

(2) For airplanes using the Cessna 680 Citation Sovereign AFM, Revision 10, dated June 30, 2011: Revise the Cessna 680 Citation Sovereign AFM, Revision 10, dated June 30, 2011, by removing the TCs identified in paragraphs (h)(2)(i) through (h)(2)(iii) of this

AD.

(i) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R10–01, dated June 30, 2011.

(ii) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R10–02, dated June 30, 2011.

(iii) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R10–03, dated June 30, 2011.

(i) Credit for Previous Actions

This paragraph provides credit for the installation required by paragraph (g) of this AD, if the installation was performed before the effective date of this AD using Cessna Service Bulletin SB680–24–11, dated December 16, 2010. (j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Wichita Aircraft Certification Office (ACO), ACE–115W, 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.

(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.

(k) Related Information

For more information about this AD, contact Nhien Hoang, Aerospace Engineer, Electrical Systems and Avionics Branch, ACE–119W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; phone: (316) 946–4190; fax: (316) 946–4107; email: nhien.hoang@faa.gov

. (l) Material Incorporated by Reference

(1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51:

(i) Cessna Service Bulletin SB680–24–11, Revision 1, dated November 15, 2011.

(ii) Cessna Temporary FAA Approved Airplane Flight Manual Change 68FM TC– R09–13, dated October 15, 2010, to the Cessna 680 Citation Sovereign Airplane Flight Manual, Revision 9, dated May 24,

2010.

(2) For service information identified in this AD, contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277; telephone 316– 517–6215; fax 316–517–5802; email citationpubs@cessna.textron.com; Internet https://www.cessnasupport.com/ newlogin.html.

(3) You may review copies of the service information at the FAA, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227–1221.

(4) You may also review copies of the service information that is incorporated by
reference at the National Archives and Records Administration (NARA). For information on the availability of this of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_ register/code

_ of

_ federal

_ regulations/
ibr

_ locations.html

. Issued in Renton, Washington, on March

22, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–7853 Filed 4–9–12; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0303; Directorate Identifier 2010–NM–214–AD; Amendment**  **39–16939; AD 2012–02–16]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 747– 100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. That AD currently requires an inspection of the
No. 2 and No. 3 windows on the left and right sides of the airplane to determine their part numbers, related investigative and corrective actions if necessary, and repetitive inspections of single pane windows. This new AD requires installing dual pane No. 2 and No. 3
windows. This new AD also removes certain airplanes from the applicability. This AD was prompted by loss of a No. 3 window in flight, which could result in consequent rapid loss of cabin pressure. Loss of the window could also
result in crew communication difficulties or incapacitation of the crew. We are issuing this AD to correct the unsafe condition on these products.

**DATES :**  This AD is effective May 15,

2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 15, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD as of September 4, 2007 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007).

**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; phone: 206–544–5000, extension 1; fax: 206–766–5680; email: me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. 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


### 21423 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations

this material at the FAA, call 425–227–

1221.

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 (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 :**  Nathan P. Weigand, Aerospace Engineer, Airframe Branch, ANM–120S,
Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6428; fax: 425–917– 6590; email: Nathan.P.Weigand@faa.gov

.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007). That AD applies to the specified products. The NPRM was published in the Federal Register on April 7, 2011 (76 FR 19278). That NPRM proposed to continue to require certain requirements of AD 2007–15–10, and proposed to require installing dual pane No. 2 and No. 3 windows. That NPRM also proposed to prohibit installed dual structural glass pane windows from being replaced with single structural glass pane windows
and to add a definition of ‘‘non-clear damage,’’ which the Accomplishment Instructions of Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010, use as criteria for window replacement. Additionally, that NPRM also proposed removing airplanes having line numbers 1418 and on from the applicability.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Support for the NPRM (76 FR 19278, April 7, 2011)

British Airways Engineering (British Airways) stated that it supports the intent of the NPRM (76 FR 19278, April 7, 2011) to replace glass number 2 and 3 windows with dual structural ply
windows.

Request To Add an Airplane System To
Alert the Air Traffic Control Tower When the Tower Is Unresponsive

An anonymous commenter requested that we change the NPRM (76 FR 19278, April 7, 2011) to add a system in the airplane to sound an alarm in the air
traffic control tower when the tower fails to respond. The change is requested due to a concern of sleeping
air traffic controllers.

We disagree with the request. The suggested change would alter the actions currently required by this AD, so additional rulemaking would be required. We find that delaying this action would be inappropriate in light
of the identified unsafe condition. We have not changed this final rule regarding this issue.

Request To Add a Statement in the NPRM (76 FR 19278, April 7, 2011) That Acrylic Windows Are Unaffected

United Airlines (United) requested we add a statement to the NPRM (76 FR 19278, April 7, 2011) indicating that not all acrylic windows are affected by this NPRM, or the six-year threshold for replacing the windows does not apply if an all-acrylic window is installed. Additionally, United requested
clarification as to whether an alternative method of compliance (AMOC) is required if an installed new window specified by the NPRM is replaced by an all-acrylic window, or if this is an acceptable procedure. As justification for its request, United stated that Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010, which was
referenced in the NPRM as the appropriate source of service information for window replacement, states that if the window is replaced with an all-acrylic window such as part number (P/N) 65B07639–( ) or P/N 65B07640–( ), no more work is

necessary.

We partially agree. Certain acrylic windows provide an equivalent level of safety as compared to the dual pane windows. We have changed paragraph(i) of this AD to include Boeingsupplied acrylic windows having P/N 65B07639–( ) and P/N 65B07640–( ) as allowable replacements for the discrepant windows. The FAA has found these windows provide an equivalent level of safety. Any other
windows will need to be evaluated on a case-by-case basis, and any operator may request approval of an AMOC to use these windows as replacements under the provisions of paragraph (l) of
this AD. Sufficient data must be
submitted to substantiate that the window would provide an acceptable level of safety.

We disagree with adding a statement to the NPRM (76 FR 19278, April 7, 2011) regarding the six-year threshold. This is already addressed in table 1 of Paragraph 1.E., ‘‘Compliance,’’ in Boeing Alert Service Bulletin 747– 56A2012, dated August 24, 2006, and Boeing Alert Service Bulletin 747– 56A2012, Revision 1, dated August 12, 2010, which state that no further action is required if acrylic window part
numbers are found. We have not changed the AD in this regard.

Request To Change Window Replacement Compliance Times

Japan Airlines requested a compliance time exception be added to paragraph (i) of the NPRM (76 FR 19278, April 7, 2011) that would allow replacement of single pane windows with dual pane windows within 22,000 flight hours, in addition to the compliance time of within 6 years after the effective date of the AD. We infer that Japan Airlines requests that the compliance time for single pane window replacement be changed to within 22,000 flight hours after new P/N 65B27042–( ) or P/N 65B27046–( ) windows were installed or within 6 years after the effective date of the AD, whichever occurs later. Japan Airlines stated its justification for this change with three reasons. First, during the repetitive inspections, it is almost impossible to detect and correct the moisture ingression into the window, which can contribute to interlayer cracks. Therefore, there are no significant issues that could result in
loss of the window. The second reason is the economic impact. The parts price of dual structural glass pane windows is almost twice that of single pane
windows. The third reason is that the operational history of the dual pane windows is unknown, and it will be
difficult to know how durable the dual pane windows will be compared to the existing single pane windows.

We disagree with changing the compliance time. We concur with the manufacturer’s compliance time stated in Boeing Service Bulletin 747– 56A2012, Revision 1, dated August 12, 2010, for dual pane window replacement. Fleet data do not support
the existence of difficulties with inspection for moisture ingression. Once


### 21424 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations

we issue this AD, any operator may request approval of an AMOC for a change of compliance time under the provisions of paragraph (l) of this AD.
Sufficient data must be submitted to substantiate that the compliance time change would provide an acceptable level of safety. We have not changed the AD in this regard.

We acknowledge the costs of the modification. However, to reduce the reliance on long-term inspections, the modification is necessary to meet an acceptable level of safety. We have not changed the AD in this regard.

Support for the NPRM (76 FR 19278, April 7, 2011) and a Request To Exempt
Certain Windows From the NPRM

British Airways requested that the NPRM (76 FR 19278, April 7, 2011) be revised to exempt windows produced by GKN under European Aviation Safety Agency (EASA) Supplemental Type Certificate (STC) EASA.A.S02838 from the six-year window replacement action specified in paragraph (i) of the NPRM. British Airways also recommended that no replacement timescale be applied to these EASA-approved parts and to allow replacement by attrition. British Airways justified its request by stating
that these GKN windows were developed to replace the discrepant windows that the NPRM proposed to replace. British Airways stated that the GKN windows have the problematic PVB or PU/PVB interlayers removed,
and have had zero removals since 2007 due to failing the inspection standards specified in Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010. British Airways also stated that in over 15 years of experience with GKN windows, the interlayer has not exhibited cracking at the hot and cold temperatures experienced by the
windows under service conditions. British Airways identified certain part numbers of the EASA-approved GKN windows and the corresponding Boeing part numbers to provide assistance to
the FAA.

We disagree with exempting windows produced by GKN from replacement. British Airways has provided useful data in support of its request. However,
we need additional information to exempt these windows from the AD. Once we issue this AD, any operator may request approval of an AMOC for
GKN window substitution under the provisions of paragraph (l) of this AD.
Sufficient data must be submitted to
substantiate that the GKN windows would provide an acceptable level of safety. We have not changed the AD in this regard.

Request To Clarify Certain Wording in NPRM (76 FR 19278, April 7, 2011)

The Boeing Company requested that we clarify certain statements in the NPRM (76 FR 19278, April 7, 2011) by changing the wording in paragraph (i) of
the NPRM from ‘‘Part 3—Window Replacement’’ to ‘‘Work Instructions, Part 3—Window Replacement;’’ and the wording in paragraph (j) of the NPRM
from ‘‘Part 2 of the Work Instructions of’’ to ‘‘Work Instructions, Part 2— Window Inspection.’’

We agree to revise the references for consistency. We have changed the wording in paragraph (i) and paragraph (j) of this AD.

Explanation of Additional Changes
Made to This AD

We have revised certain paragraph headers throughout this AD.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously.
We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (76 FR 19278, April 7, 2011) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (76 FR 19278, April 7, 2011).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Costs of Compliance

We estimate that this AD affects 144 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection to determine window part numbers;

retained from existing AD. 4 work-hours × $85 per hour = $340 ................... $0 $340 $48,960

Detailed inspection, if necessary; retained from

existing AD. 1 work-hour × $85 per hour = $85 ....................... 0 85 12,240

Dual pane window replacement; new action ........ 16 work-hours × $85 per hour = $1,360 .............. 44,014 45,374 6,533,856

We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Window replacement ...................................... 16 work-hours × $85 per hour = $1,360 ............................................ $44,014 $45,374

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


### 21425 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations

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),

(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**

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

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

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007), and adding the following new AD:

2012–02–16 The Boeing Company: Amendment 39–16939; Docket No. FAA–2011–0303; Directorate Identifier

2010–NM–214–AD.

(a) Effective Date

This airworthiness directive (AD) is effective May 15, 2012. (b) Affected ADs
This AD supersedes AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007).

(c) Applicability

This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 56, Windows.

(e) Unsafe Condition

This AD was prompted by loss of a No. 3 window in flight, which could result in consequent rapid loss of cabin pressure. We are issuing this AD to detect and correct cracking in the fail-safe interlayer of certain No. 2 and No. 3 glass windows, which could result in loss of the window and consequent rapid loss of cabin pressure. Loss of the
window could also result in crew communication difficulties or incapacitation
of the crew.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Requirements With New Service
Information

This paragraph restates the requirements of paragraph (f) of AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007), with new service information. Inspect
the No. 2 and No. 3 windows on the left and right sides of the airplane to determine their part numbers, and do all the applicable related investigative and corrective actions, by accomplishing all of the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–56A2012, dated August 24, 2006; or Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010; except as required by paragraph (j) of this AD; as applicable. Do all of these actions at the compliance times specified in Tables 1, 2, and 3 of paragraph 1.E. of Boeing Alert Service Bulletin 747– 56A2012, dated August 24, 2006; or Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010; as applicable; except as provided by paragraph (h) of this AD. A review of airplane maintenance records is acceptable in lieu of the inspection if the part numbers of the windows can be conclusively determined from that review. Repeat the related investigative and corrective actions thereafter at the interval specified in Table 2 or 3 of paragraph 1.E. of Boeing Alert Service Bulletin 747–56A2012, dated August 24, 2006; or Boeing Service Bulletin 747– 56A2012, Revision 1, dated August 12, 2010; except as required by paragraph (h) of this AD, as applicable. As of the effective date of this AD, only Boeing Service Bulletin 747– 56A2012, Revision 1, dated August 12, 2010, except as required by (j) of this AD, may be used. Replacing a window in accordance with paragraph (i) of this AD terminates the requirements of this paragraph for that
window.

(h) Retained Exception to Compliance Times

This paragraph restates the exceptions to the compliance times specified in paragraph (g) of AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007). Where Tables 1, 2, and 3 of paragraph 1.E. of Boeing Alert Service Bulletin 747–56A2012, dated August 24, 2006, specify counting the compliance time from ‘‘* * * after the date on this service bulletin,’’ this AD requires counting the compliance time from September 4, 2007 (the effective date of AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007)). After replacing a discrepant window with a new window having part number (P/N) 65B27042–( ), 65B27043–( ), 65B27046–( ), or 65B27047– ( ), do the initial detailed inspection required in paragraph (g) of this AD of the new window at the applicable compliance time: (1) Within 5,500 flight hours after installing P/N 65B27042–( ) or 65B27043–( ), or (2) Within 22,000 flight hours after installing P/ N 65B27046–( ) or 65B27047–( ).

(i) New Requirements of This AD: Window Replacement

Within 6 years after the effective date of this AD, replace all No. 2 windows having P/N 65B27042–( ) or 65B27046–( ) with windows having P/N 141U4821–( ), 141U4822–( ), or 65B07639–( ); and replace all No. 3 windows having P/N 65B27043–( ) or 65B27047–( ) with windows having P/N 141U4831–( ), 141U4832–( ), or 65B07640– ( ), in accordance with ‘‘Work Instructions, Part 3—Window Replacement,’’ of the Accomplishment Instructions of Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010. Doing this replacement for all windows terminates the actions required by paragraphs (g) and (h) of
this AD.

(j) New Requirements of This AD: Non-Clear Damage Definition and Action

Where Step 4.e., ‘‘Work Instructions, Part 2—Window Inspection,’’ of the Accomplishment Instructions in Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010, specifies ‘‘non-clear damage’’ as a criterion for window replacement, this AD defines non-clear damage to be any degradation of the transparency of the window, which would
hinder the internal or external detailed inspections for fail-safe interlayer cracks, glass pane cracks and chips, and indicationsof electrical arcing. Replacement for nonclear damage is required by this AD only if the non-clear damage hinders the inspection for fail-safe interlayer cracks, glass pane cracks and chips, or indications of electrical arcing.


### 21426 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations

(k) Parts Installation

As of the effective date of this AD, do not install any No. 2 or No. 3 window having P/ N 65B27042–( ), 65B27043–( ), 65B27046– ( ), or 65B27047–( ) that is not new or on which the window flight hours are not known, on any airplanes, unless the actions specified in paragraph (g) of this AD are
done.

(l) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office, 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: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.

(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.

(4) AMOCs previously approved in accordance with AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007), are approved as AMOCs for the corresponding provisions of this AD except previous AMOCs approving window replacement that do not specify installing dual structural glass pane windows are not considered approved for corresponding inspection methods required by this AD.

(m) Related Information

For more information about this AD, contact Nathan P. Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov.

(n) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part

51.

(2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on May 15, 2012.

(i) Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010.

(4) The following service information was approved for IBR on September 4, 2007 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007).

(i) Boeing Alert Service Bulletin 747– 56A2012, dated August 24, 2006.

(5) 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; phone: 206–544–5000, extension 1; fax: 206–766– 5680; email: me.boecom@boeing.com;

Internet: https://www.myboeingfleet.com.

(6) 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.

(7) You may also review copies of the service information that is incorporated by
reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_ register/code

_ of

_ federal

_ regulations/
ibr

_ locations.html.

Issued in Renton, Washington, on January

23, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–8452 Filed 4–9–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0915; Directorate Identifier 2011–NM–020–AD; Amendment**  **39–17013; AD 2012–07–07]**

**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 747 airplanes. This AD was prompted by reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. This AD requires repetitive general visual inspections for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections for cracking of the latch pins; and corrective actions if necessary. We are issuing this AD to detect and correct fractured or broken latch pins, which could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane.

**DATES :**  This AD is effective May 15,

2012.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 15, 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, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email me.boecom@boeing.com ; Internet https://www.myboeingfleet.com. 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 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 (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 :**  Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; email: nathan.p.weigand@faa.gov

.
**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 was published in the Federal Register on September 1, 2011 (76 FR 54405). That NPRM proposed to require repetitive general visual inspections for broken or missing latch pins of the
lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections for cracking of the latch pins; and corrective actions if necessary.