Document ID: FAA-2008-0375-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Short Brothers Model SD3-60 Airplanes
Posted Date: 2008-04-01T04:00Z

[Federal Register: April 1, 2008 (Volume 73, Number 63)]
[Proposed Rules]               
[Page 17260-17263]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap08-11]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0375; Directorate Identifier 2007-NM-272-AD]
RIN 2120-AA64

 
Airworthiness Directives; Short Brothers Model SD3-60 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede two existing airworthiness 
directives (ADs) that apply to all Short Brothers Model SD3-60 
airplanes. One of the ADs currently requires inspection of the welded 
joints of the balance weight brackets for the elevator trim tabs for 
cracking; repetitive inspections, as applicable; and corrective actions 
including the eventual replacement of all brackets. The other AD 
currently requires, for certain airplanes, repetitive inspections for 
cracking of the balance weight brackets and replacement of any cracked 
bracket, and provides for an optional terminating action for the 
repetitive inspections. This proposed AD would require an additional 
inspection to detect cracks of the balance weight brackets, applicable 
related investigative and corrective actions, and replacement of a 
certain balance weight bracket when it has reached its maximum life 
limit. This proposed AD results from a report indicating that several 
reworked balance weight brackets have exhibited signs of premature 
failure. We are proposing this AD to prevent failure of the balance 
weight brackets of the elevator trim tabs, which could cause loss of 
the balance weight. This could result in incorrect trim during takeoff 
and landing, and reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 1, 2008.

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 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Short 
Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport 
Road, Belfast BT3 9DZ, Northern Ireland.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket 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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; 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-2008-0375; 
Directorate Identifier 2007-NM-272-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 because of 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 June 16, 2004, we issued AD 2004-13-08, amendment 39-13690 (69 
FR 38813, June 29, 2004), for all Short Brothers Model SD3-60 
airplanes. That AD requires inspection of the welded joints of the 
balance weight brackets for the left and right elevator trim tabs for 
cracking; repetitive inspections, as applicable; and corrective actions 
including the eventual replacement of all brackets, which constitutes 
terminating action for the repetitive inspections. That AD resulted 
from a report indicating that a balance weight assembly for an elevator 
trim tab detached during landing. We issued that AD to prevent the loss 
of the balance weight for the elevator trim tab, which could result in 
incorrect trim during takeoff and landing, and reduced controllability 
of the airplane.
    On February 11, 2005, we issued AD 2005-04-13, amendment 39-13985 
(70 FR 9212, February 25, 2005), for all Short Brothers Model SD3-60 
airplanes. That AD requires, for certain airplanes, repetitive 
inspections for cracking of the balance weight brackets of the elevator 
trim tabs, and replacement of any cracked bracket with a new or 
reworked bracket that conforms to the approved design standard. That AD 
also provides for an optional terminating action for the repetitive 
inspections. That AD resulted from reports indicating that balance 
weight brackets (which might have been installed in accordance with AD 
2004-13-08) have been found cracked on both the left and right elevator 
trim tabs. We issued that AD to prevent failure of the balance weight 
bracket for the elevator trim tab, which could cause loss of the 
balance weight.

[[Page 17261]]

This could result in incorrect trim during takeoff and landing, and 
reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2005-04-13, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has informed us that a batch of non-conforming 
balance weight brackets of the elevator trim tabs, manufactured in 2003 
and 2004, were reworked by the manufacturer. These balance weight 
brackets were considered as fully conforming brackets and were 
installed in accordance with AD 2005-04-13. Several of these reworked 
balance weight brackets exhibited signs of premature failure. The 
premature failures were attributed to the welding operations required 
as part of the rework. Testing confirmed a reduced service life for the 
balance weight brackets. Failure of the balance weight brackets of the 
elevator trim tabs, if not corrected, could cause loss of the balance 
weight. This could result in incorrect trim during takeoff and landing, 
and reduced controllability of the airplane.

Relevant Service Information

    Shorts has issued Alert Service Bulletins SD360-55-A21, Revision 1, 
dated March 29, 2007; and SD360-55-20, Revision 2, dated March 29, 
2007. The service bulletins describe new procedures for a dye penetrant 
inspection to detect cracks of certain balance weight brackets of the 
elevator trim tabs, and applicable related investigative and corrective 
actions. The related investigative actions involve repeating the 
inspection described previously. The corrective action involves 
replacing any cracked balance weight bracket with a new bracket. The 
service bulletins also describe procedures for eventual replacement of 
certain balance weight brackets with new brackets, when they have 
reached their maximum life limit (i.e., 1,750 or 28,800 flight hours 
depending on the airplane configuration). Accomplishing the replacement 
would eliminate the need for the repetitive dye penetrant inspections 
described previously and the repetitive inspections required by ADs 
2004-13-08 and 2005-04-13.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued emergency airworthiness directive 
2007-0107-E, dated April 18, 2007, to ensure the continued 
airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in the United Kingdon and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede ADs 2004-13-08 and 2005-04-13 and 
would retain the requirements of the existing ADs. This proposed AD 
also would require accomplishing the actions specified in service 
bulletins described previously.

Differences Between the Proposed AD and EASA Airworthiness Directive

    Although the EASA emergency airworthiness directive 2007-0107-E 
does not list a grace period for certain compliance times, this 
proposed AD adds a grace period to those compliance times. We find that 
a grace period will keep airplanes from being grounded unnecessarily.

Change to Existing ADs

    This proposed AD would retain all requirements of ADs 2004-13-08 
and 2005-04-13. Since AD 2004-13-08 was issued, the AD format has been 
revised, and certain paragraphs have been rearranged. In addition, the 
need to supersede two ADs requires that we re-identify the paragraphs 
for AD 2005-04-13. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following tables:

             Revised Paragraph Identifiers for AD 2004-13-08
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2004-13-08              in this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
paragraph (d).............................  paragraph (i).
paragraph (e).............................  paragraph (j).
paragraph (f).............................  paragraph (k).
------------------------------------------------------------------------

             Revised Paragraph Identifiers for AD 2005-04-13
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2005-04-13              in this proposed AD
------------------------------------------------------------------------
paragraph (f).............................  paragraph (l).
paragraph (g).............................  paragraph (m).
paragraph (h).............................  paragraph (n).
paragraph (i).............................  paragraph (o).
paragraph (j).............................  paragraph (p).
------------------------------------------------------------------------

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                 Number of
                                                          Average                                                  U.S.-
                  Action                    Work hours   labor rate     Parts           Cost per airplane        registered           Fleet cost
                                                          per hour                                               airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2004-13-08)..           12          $80         None  $960, per inspection cycle..           21  $20,160, per inspection
                                                                                                                              cycle.
Replacement (required by AD 2004-13-08)..            8           80         $632  $1,272......................           21  $26,712.
Inspections (required by AD 2005-04-13)..           12           80         None  $960, per inspection cycle..           21  $20,160, per inspection
                                                                                                                              cycle.
Inspection (new proposed action).........           12           80         None  $960, per inspection cycle..           21  $20,160, per inspection
                                                                                                                              cycle.
Replacement (new proposed action)........            8           80         $864  $1,504, per replacement                21  $31,584, per replacement
                                                                                   cycle.                                     cycle.
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[[Page 17262]]

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 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 that the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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, 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.

Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendments 39-13690 (69 FR 38813, June 29, 2004) and 39-13985 
(70 FR 9212, February 25, 2005) and by adding the following new 
airworthiness directive (AD):

Short Brothers PLC: Docket No. FAA-2008-0375; Directorate Identifier 
2007-NM-272-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 1, 
2008.

Affected ADs

    (b) This AD supersedes ADs 2004-13-08 and 2005-04-13.

Applicability

    (c) This AD applies to all Short Brothers Model SD3-60 
airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report indicating that several 
reworked balance weight brackets have exhibited signs of premature 
failure. We are issuing this AD to prevent failure of the balance 
weight bracket of the elevator trim tab, which could cause loss of 
the balance weight. This could result in incorrect trim during 
takeoff and landing, 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.

Requirements of AD 2004-13-08

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in paragraphs (g) 
through (j) of this AD, means the Accomplishment Instructions of 
Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; or 
Revision 01, dated June 20, 2005.

Initial Inspection

    (g) Within 2 months after August 3, 2004 (the effective date of 
AD 2004-13-08): Do a dye penetrant inspection for cracking in the 
welded joints of the balance weight brackets for the left and right 
elevator trim tabs, in accordance with the service bulletin.

Investigative and Corrective Actions if No Cracking is Found

    (h) If no cracking is found during the inspection required by 
paragraph (g) of this AD, do the actions required by paragraphs 
(h)(1) and (h)(2) of this AD at the applicable compliance times.
    (1) Repeat the inspection required by paragraph (g) of this AD 
at intervals not to exceed 4,800 flight hours until the bracket is 
replaced per paragraph (h)(2) or (i) of this AD.
    (2) Prior to the accumulation of 28,800 total flight hours, or 
within 6 months after August 3, 2004, whichever occurs later: 
Replace any bracket that has not been replaced per paragraph (i) of 
this AD with a new bracket or with a serviceable bracket that has 
been inspected in accordance with paragraph (g) of this AD. Replace 
in accordance with the service bulletin. Replacement of the brackets 
constitutes terminating action for the repetitive inspections 
required by paragraph (h)(1) of this AD.

Corrective Actions if Any Cracking is Found

    (i) If any cracking is found during any inspection required by 
paragraph (g) or (h) of this AD: Before further flight, accomplish 
the applicable action in paragraph (i)(1) or (i)(2) of this AD in 
accordance with the service bulletin.
    (1) For airplanes that have accumulated less than 28,800 flight 
hours and on which all cracking on brackets is less than 0.25 inch 
in length: Repair the affected bracket in accordance with Part B of 
the service bulletin (including the additional dye penetrant 
inspection of the repaired welded joint) and repeat the inspection 
required by paragraph (g) of this AD at intervals not to exceed 
4,800 flight hours; or replace the bracket in accordance with 
paragraph (h)(2) of this AD. Replacement of the bracket constitutes 
terminating action for the repetitive inspections.
    (2) For any airplane on which any cracking on a bracket is 0.25 
inch in length or greater, and for any airplane that has accumulated 
28,800 flight hours or more on which any cracking of any length is 
found on a bracket: Replace the affected bracket with a new bracket 
or with a serviceable bracket that has been inspected in accordance 
with paragraph (g) of this AD. Replacement of the bracket 
constitutes terminating action for the repetitive inspections 
required by paragraph (i)(1) of this AD.

Refitting

    (j) Before further flight following any inspection per paragraph 
(g) or (h) of this AD; or before further flight following repair or 
replacement of a bracket per paragraphs (h)(2) or (i) of this AD: 
Refit the balance weights, covers, and trim tabs, in accordance with 
the service bulletin. Where the service bulletin specifies to 
contact the manufacturer for disposition of certain conditions while 
refitting, obtain further disposition instructions from the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Civil Aviation Authority (CAA) (or its delegated agent).

Parts Installation

    (k) As of August 3, 2004, no person may install on any airplane 
a balance weight bracket unless the welded joint has been inspected 
in accordance with paragraph (g) of this AD.

Requirements of AD 2005-04-13

Service Bulletin Reference

    (l) The following information applies to the service bulletin 
referenced in paragraphs (l) through (o) of this AD:
    (1) The term ``service bulletin,'' as used in paragraphs (l) 
through (o) of this AD, means

[[Page 17263]]

the Accomplishment Instructions of Short Brothers Alert Service 
Bulletin SD360-55-A21, dated December 16, 2004.
    (2) Although the service bulletin specifies to return subject 
parts to the manufacturer, this AD does not include that 
requirement.

Repetitive Inspections

    (m) For airplanes equipped with balance weight brackets of the 
elevator trim tabs having part number SD3-07-6011xA, and having a 
serial number beginning with ``X3'' or ``X4'': Prior to the 
accumulation of 250 flight hours since installation of the subject 
balance weight bracket of the elevator trim tab, or within 30 flight 
hours after March 14, 2005 (the effective date of AD 2005-04-13), 
whichever is later, do a dye penetrant inspection for cracking of 
the balance weight brackets for the left and right elevator trim 
tabs, in accordance with the service bulletin.
    (1) For a balance weight bracket on which no cracking is found: 
Do paragraph (o) of this AD, and repeat the inspection thereafter at 
intervals not to exceed 250 flight hours until paragraph (n) of this 
AD is accomplished.
    (2) For a balance weight bracket on which any cracking is found: 
Before further flight, replace the bracket with a new or reworked 
balance weight bracket that conforms to the approved design standard 
in accordance with the service bulletin, and do paragraph (o) of 
this AD.

Optional Terminating Action

    (n) For airplanes equipped with balance weight brackets of the 
elevator trim tabs having part number SD3-07-6011xA, and having a 
serial number beginning with ``X3'' or ``X4'': Replacement of any 
subject balance weight bracket with a new or reworked balance weight 
bracket that conforms to the approved design standard, in accordance 
with the service bulletin, constitutes terminating action for the 
repetitive inspections required by paragraph (m) of this AD for the 
replaced bracket.

Refitting

    (o) For airplanes equipped with balance weight brackets of the 
elevator trim tabs having part number SD3-07-6011xA, and having a 
serial number beginning with ``X3'' or ``X4'': Before further flight 
following any inspection or replacement of a bracket in accordance 
with paragraphs (m) and (n) of this AD: Refit the balance weights, 
covers, and trim tabs, in accordance with the service bulletin. 
Where the service bulletin specifies to contact the manufacturer for 
disposition of certain conditions while refitting, obtain further 
disposition instructions from the Manager, International Branch, 
ANM-116, FAA, Transport Airplane Directorate; or the Civil Aviation 
Authority (CAA) (or its delegated agent).

Parts Installation

    (p) For all airplanes: As of March 14, 2005, no person may 
install, on any airplane subject to this AD, a balance weight 
bracket having part number SD3-07-6011xA, and having a serial number 
beginning with ``X3'' or'' X4,'' unless the bracket is also marked 
``Rework batch number R-Bxxxxx'' (where ``xxxxx'' is a number).

New Requirements of This AD

Inspection(s) and Replacements

    (q) For airplanes equipped with balance weight brackets of the 
elevator trim tabs having part number SD3-07-6011xA manufactured in 
the year 2003 or 2004, including re-worked brackets, installed in 
accordance with paragraph (h)(2), (i)(2), or (n) of this AD, as 
applicable: Do the actions specified in paragraphs (q)(1) and (q)(2) 
of this AD in accordance with Parts A and B of the Accomplishment 
Instructions of Shorts Alert Service Bulletin SD360-55-A21, Revision 
1, dated March 29, 2007.
    (1) Within 30 flight hours after the effective date of this AD, 
or within 250 flight hours since installation of the balance weight 
brackets of the elevator trim tabs or since the last inspection 
required by paragraph (g), (h)(1), (i)(1), or (m) of this AD, 
whichever occurs later: Do a dye penetrant inspection to detect 
cracks of the balance weight brackets of the elevator trim tabs.
    (i) If no crack is detected, repeat the dye penetrant inspection 
at intervals not to exceed 250 flight hours, until the replacement 
required by paragraph (q)(2) of this AD is done.
    (ii) If any crack is detected, before further flight, do the 
replacement specified in paragraph (q)(2) of this AD.
    (2) Before the accumulation of 1,750 flight hours since 
installation of the balance weight brackets of the elevator trim 
tabs, or within 180 days after the effective date of this AD, 
whichever occurs later: Replace the balance weight brackets with new 
balance weight brackets manufactured in 2005 or later. Thereafter, 
replace any balance weight bracket with a new bracket manufactured 
in 2005 or later at intervals not to exceed the accumulation of 
1,750 flight hours on that bracket. Accomplishment of the initial 
replacement ends the repetitive inspection requirements of this AD.
    (r) For airplanes equipped with balance weight brackets of the 
elevator trim tabs having part number SD3-31-6213xB inspected in 
accordance with paragraph (g), (h)(1), or (i)(1) of this AD and 
retained or refitted following approved repair in accordance with 
paragraph (j) of this AD: Do the actions specified in paragraphs 
(r)(1) and (r)(2) of this AD in accordance with Parts A and B of the 
Accomplishment Instructions of Shorts Alert Service Bulletin SD360-
55-20, Revision 2, dated March 29, 2007.
    (1) Within 4,800 flight hours since last inspection, or within 
180 days after the effective date of this AD, whichever occurs 
later, and thereafter at intervals not to exceed 4,800 flight hours: 
Do a dye penetrant inspection to detect cracks of the balance weight 
brackets of the elevator trim tabs.
    (i) If no crack is detected, repeat the dye penetrant inspection 
at intervals not to exceed 4,800 flight hours, until the replacement 
required by paragraph (r)(2) of this AD is done.
    (ii) If any crack is detected, before further flight, do the 
replacement specified in paragraph (r)(2) of this AD.
    (2) Before the accumulation of 28,800 flight hours since any 
balance weight bracket of the elevator trim tabs is new, or within 
180 days after the effective date of this AD, whichever occurs 
later: Replace the balance weight brackets with new balance weight 
brackets manufactured in 2005 or later. Thereafter, replace any 
balance weight bracket with a new bracket manufactured in 2005 or 
later at intervals not to exceed the accumulation of 28,800 flight 
hours on that bracket. Accomplishment of the initial replacement 
ends the repetitive inspection requirements of this AD.

Part Installation

    (s) For all airplanes: As of the effective date of this AD, no 
person may install, on any airplane, a balance weight bracket of the 
elevator trim tab manufactured earlier than 2005.

Alternative Methods of Compliance (AMOCs)

    (t)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, 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.

Related Information

    (u) EASA emergency airworthiness directive 2007-0107-E, dated 
April 18, 2007, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-6614 Filed 3-31-08; 8:45 am]

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