## 62653 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules

Credit for Actions Accomplished in Accordance with Previous Service Information

(j) Replacements done before the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–78– 1074, dated April 7, 2005, are acceptable for compliance with the requirements of paragraph (h) of this AD.
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 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 e-mailed 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.

Related Information

(l) For more information about this AD, contact Chris Parker, Aerospace Engineer, Propulsion Branch, ANM–140S, 1601 Lind Avenue, SW., Renton, Washington 98057–
3356; phone: 425–917–6496; fax: 425–917– 6590; e-mail: chris.r.parker@faa.gov.

(m) 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; e-mail 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.

Issued in Renton, Washington, on September 30, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–26104 Filed 10–7–11; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1060; Directorate Identifier 2011–NM–015–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A310 Series Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Within the scope of the Fuel System Safety Program (FSSP), analyses of the wire routing showed that the route 2S of the fuel electrical circuit in the Right Hand (RH) wing must be modified in order to ensure better segregation between fuel quantity indication wires and the 115 Volts Alternating Current (VAC) wires of route 2S.

This condition, if not corrected, could result in short circuits leading to arcing, and possible fuel tank explosion.


### * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES** 

### : We must receive comments on this proposed AD by November 25,
2011.

**ADDRESSES** 

### : You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus SAS– EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.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 Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT**

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### :
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2011–1060; Directorate Identifier 2011–NM–015–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On January 3, 2008, we issued AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008). That AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008), we have determined


## 62654 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules

that the route 2S of the fuel electrical circuit in the right hand wing must be modified to ensure better segregation between fuel quantity indication wires and the 115 volts alternating current wires of route 2S. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0005, dated January 17, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Within the scope of the Fuel System Safety Program (FSSP), analyses of the wire routing showed that the route 2S of the fuel electrical circuit in the Right Hand (RH) wing must be modified in order to ensure better segregation between fuel quantity indication wires and the 115 Volts Alternating Current (VAC) wires of route 2S.

This condition, if not corrected, could result in short circuits leading to arcing, and possible fuel tank explosion.

To address this unsafe condition, [Direction Ge  ́ ne

 ́rale de l’Aviation Civile] DGAC France issued AD 2002–578(B) [which corresponds to FAA AD 2004–15–16, Amendment 39–13750 (69 FR 45578, July 30, 2004)] to require improvements of the design as specified in Airbus Service Bulletin (SB) A310–28–2148 original issue or Revision 01. EASA AD 2007–0230 [which corresponds to FAA AD 2008–01–05 (73 FR 2795, January 16, 2008)], which superseded DGAC France AD 2002–578(B), required those same actions, plus additional work as defined in Airbus SB A310–28–2148 Revision 02.

Since EASA AD 2007–0230 was issued, an operator reported the possibility of chafing with the new routing of the wire bundle 2S in the RH wing pylon area to the generator wire bundle of engine 2. The modification of this zone was introduced by A310–28–2148 Revision 02 as additional work. Investigation showed that, to avoid the risk of chafing, the affected wiring harnesses must be installed at a higher position to provide sufficient clearance with the newly routed wire bundle 2S conduit.

Airbus published Revision 03 of SB A310– 28–2148 to describe these changes, but a new interference has been found and requires updating SB A310–28–2148 to Revision 04 [or 05].

For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2007–0230, which is superseded, and requires the additional work as specified in Revision 04 [or 05] of Airbus SB A310–28–
2148. 

### Required actions include modifying the wire routings and installing a modified bracket. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued Mandatory Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance

We estimate that this proposed AD would affect 61 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD.



### TABLE

### —E STIMATED 

### COSTS

Action Work hours Average labor rate per hour Parts Cost per airplane Number of U.S.- registered airplanes Fleet cost

Modification (required by AD 2004–15–16, Amendment 39-13750

(69 FR 45578, July 30, 2004)) ....................................................... 35 $85 $4,459 $7,434 68 $505,512 Modification (required by AD 2008–01–05, Amendment 39-15330

(73 FR 2795, January 16, 2008)) .................................................. 22 85 1,870 3,740 68 254,320 Modification (new proposed action) ................................................... 62 85 2,210 7,480 61 456,280



### 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under the 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.


## 62655 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 Amendment 39–15330 (73 FR 2795, January 16, 2008) and adding the following new AD:

Airbus: Docket No. FAA–2011–1060; Directorate Identifier 2011–NM–015–AD.

Comments Due Date

(a) We must receive comments by November 25, 2011.

Affected ADs

(b) This AD supersedes AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008).
Applicability

(c) This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category; all serial numbers.
Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Within the scope of the Fuel System Safety Program (FSSP), analyses of the wire routing showed that the route 2S of the fuel electrical circuit in the Right Hand (RH) wing must be modified in order to ensure better segregation between fuel quantity indication wires and the 115 Volts Alternating Current (VAC) wires of route 2S.

This condition, if not corrected, could result in short circuits leading to arcing, and possible fuel tank explosion.


### * * * * *
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2004– 15–16 Amendment 39–13750 (69 FR 45578, July 30, 2004), With New Service Information

Modification

(g) For all airplanes except airplanes on which Airbus Service Bulletin A310–28– 2148, Revision 02, dated March 9, 2007, has been done (Airbus Modifications 12427 and 12435): Within 4,000 flight hours after September 3, 2004 (the effective date of AD 2004–15–16 (69 FR 45578, July 30, 2004)), modify the routing of wires in the RH wing by installing cable sleeves, per the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 01, dated October 29, 2002; Revision 02, dated March 9, 2007; or Revision 05, dated August 3, 2010. As of February 20, 2008 (the effective date of AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008)), Revision 02 must be used. As of the effective date of this AD, Revision 05 must be used.
Actions Accomplished Previously

(h) Modification of the routing of wires accomplished before September 3, 2004, per Airbus Service Bulletin A310–28–2148, dated January 23, 2002, is acceptable for compliance with the corresponding requirements of paragraph (g) of this AD.
Restatement of Requirements of AD 2008– 01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008), With New Service Information

Modification (Additional Work)

(i) For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, dated January 23, 2002; or Airbus Service Bulletin A310–28–2148, Revision 01, dated October 29, 2002; have been done before February 20, 2008, except for airplanes on which Airbus Service Bulletin A310–28– 2148, Revision 02, dated March 9, 2007, has been done (Airbus Modifications 12427 and 12435): Within 6,000 flight hours or 30 months after February 20, 2008, whichever occurs first, perform further modification by installing additional protection sleeves in the outer wing area near the cadensicon sensor and segregating wire route 2S in the RH pylon area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 02, dated March 9, 2007; or Revision 05, dated August 3, 2010. As of the effective date of this AD, Revision 05 must be used.
New Requirements of This AD

Additional Modification/Installation for Certain Airplanes

(j) For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, Revision 02, dated March 9, 2007, have been accomplished, and do not have production modification 07633 and on which Airbus Service Bulletin A310–36–2015 has not been done: Within 6,000 flight hours or 30 months after the effective date of this AD, whichever occurs first, modify the wire routings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010.

(k) For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, Revision 02, dated March 9, 2007, have been accomplished, and have production modification 07633 or on which Airbus Service Bulletin A310–36–2015 has been done: Within 1,000 flight hours after the effective date of this AD, install a modified bracket, in accordance with paragraph 3.B.(7) ‘‘Additional Work 2’’ of the Accomplishment Instructions of Airbus Service Bulletin A310– 28–2148, Revision 05, dated August 3, 2010.

(l) For airplanes on which the actions specified in Airbus Service Bulletin A310– 28–2148, Revision 03, dated June 2, 2009, have been accomplished; and have modification 07633 done in production or on which the actions specified in Airbus Service Bulletin A310–36–2015 have been done; no further action is required by this AD.
Credit for Actions Accomplished in Accordance With Previous Service Information

(m) Modifications done in accordance with Airbus Service Bulletin A310–28–2148, Revision 04, dated April 14, 2010, before the effective date of this AD are acceptable for compliance with the corresponding modification required by paragraph (g), (i), (j), and (k) of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(n) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9- ANM-116-AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2008–01–05, Amendment 39–15330 (73 FR 2795, January 16, 2008), are approved as AMOCs for the corresponding provisions of this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they


## 62656 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules

are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(o) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0005, dated January 17, 2011; and Airbus Service Bulletin A310–28–2148, Revision 05, dated August 3, 2010; for related information.

Issued in Renton, Washington, on September 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–26106 Filed 10–7–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1062; Directorate Identifier 2011–NM–038–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Saab AB, **Saab Aerosystems Model 340A (SAAB/ SF340A) and SAAB 340B Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

In 2003, a number of reports had been received concerning broken wires and corroded connectors in the SAAB 340 main landing gear (MLG) emergency release system. The investigation results showed that these were due to improper repairs and installations, not conforming to the approved type design.

This condition, if not corrected, could inhibit the functioning of the separation bolt, preventing proper release of the MLG during an emergency situation, possibly resulting in damage to aeroplane during landing and injury to the occupants.


### * * * * *

The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES** 

### : We must receive comments on this proposed AD by November 25,
2011. **ADDRESSES** 

### : You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Saab AB, Saab Aerosystems, SE–581 88, Linko  ̈ ping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; e-mail saab2000.techsupport@saabgroup.com; Internet http://www.saabgroup.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 Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT**

### : Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### :
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2011–1062; Directorate Identifier 2011–NM–038–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On May 28, 2004, we issued AD 2004–12–03, Amendment 39–13662 (69 FR 35235, June 24, 2004). That AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2004–12–03, Amendment 39–13662 (69 FR 35235, June 24, 2004), we have received reports that the previous modification does not fully meet the expected results; therefore, an improved separation bolt harness having part number (P/N) 7292520–691 has been designed to replace the current separation bolt harness having P/N 7292520–678. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0003, dated January 17, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

In 2003, a number of reports had been received concerning broken wires and corroded connectors in the SAAB 340 main landing gear (MLG) emergency release system. The investigation results showed that these were due to improper repairs and installations, not conforming to the approved type design.

This condition, if not corrected, could inhibit the functioning of the separation bolt, preventing proper release of the MLG during an emergency situation, possibly resulting in damage to aeroplane during landing and injury to the occupants.

To address that unsafe condition, Swedish AD (SAD) 1–186 was issued to require an inspection and, depending on findings, corrective action, in accordance with SAAB Service Bulletin (SB) 340–32–127.

Subsequently, Saab introduced a modification to ensure correct functioning of the MLG emergency release system. Accomplishment of that modification (SAAB SB 340–32–128) was made mandatory by SAD 1–189 [which corresponds to FAA AD 2004–12–03 (69 FR 35235, June 24, 2004)].

Since that [SAD] AD was issued, service experience has shown that this modification does not fully meet the expected results.

Prompted by these findings, SAAB has developed an improved separation bolt harness with a new routing.

For the reasons described above, this AD requires replacement of the current