Airworthiness Directives; Boeing Model 727-100 Series Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA8472SW

[Federal Register Volume 62, Number 213 (Tuesday, November 4, 1997)]
[Rules and Regulations]
[Pages 59565-59566]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-29114]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-268-AD; Amendment 39-10190; AD 97-23-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727-100 Series Airplanes 
Modified in Accordance With Supplemental Type Certificate (STC) 
SA8472SW

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Boeing Model 727-100 series airplanes. This 
action requires a revision to the Airplane Flight Manual (AFM) to 
prohibit stabilized operation between 60 and 75 percent N1 speed during 
ground operations in reverse or forward thrust. This amendment is 
prompted by a report that, during preparation for takeoff, a transport 
category airplane equipped with Rolls-Royce Tay 650-15 engines 
sustained an engine fan blade failure, followed by an engine fire. The 
actions specified in this AD are intended to prevent uncontained 
failure of engine fan blades due to high cycle fatigue cracking, which 
could result in loss of thrust from the affected engine and secondary 
damage to the airplane and/or fire.

DATES: Effective November 19, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 19, 1997.
    Comments for inclusion in the Rules Docket must be received on or 
before January 5, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 97-NM-268-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The Airplane Flight Manual (AFM) Supplement referenced in this AD 
may be obtained from the Dee Howard Company, P.O. Box 469001, San 
Antonio, Texas 78246. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Rotorcraft Directorate, 2601 Meacham 
Boulevard, Fort Worth, Texas; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ron Filler, Flight Test Pilot, 
Airplane Certification Office, ASW-150, FAA, Rotorcraft Directorate, 
2601 Meacham Boulevard, Fort Worth, Texas, 76137-4298; telephone (817) 
222-5132; fax (817) 222-5960.

SUPPLEMENTARY INFORMATION: The Rijksluchtvaartdienst (RLD), which is 
the airworthiness authority for the Netherlands, recently notified the 
FAA that it received a report indicating that, during preparation for 
takeoff, a Fokker Model F28 Mark 0100 series airplane equipped with 
Rolls-Royce Tay 650-15 engines sustained an engine fan blade failure, 
followed by an engine fire.
    Investigation revealed that five fan blades failed at the root 
area, three fan blades failed at mid-height, and the remainder were 
damaged severely. Further investigation revealed that all five fan 
blades failed due to rapid high cycle fatigue cracking with low cycle 
fatigue cracking origin. Evidence of rapid high cycle fatigue cracking 
indicates that an operational effect is causing high vibratory 
stresses. Rolls-Royce considers that the high cycle fatigue cracking 
was caused by vibration during previous thrust reverser applications.
    Upon further investigation, the FAA has determined that Boeing 
727QF airplanes have engine installation and service records that are 
similar to Fokker Model F28 Mark 0100 series airplanes. Boeing 727QF 
airplanes are Boeing Model 727-100 airplanes that have been modified in 
accordance with Supplemental Type Certificate (STC) SA8472SW, which 
includes the installation of Rolls-Royce Tay 651-54 engines.
    The FAA has evaluated these findings and has determined that high-
cycle fatigue cracking of the engine fan blades could cause uncontained 
failure of the engine fan blades. Such fatigue cracking, if not 
corrected, could result in loss of thrust from the affected engine and 
secondary damage to the airplane and/or fire.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Dee Howard Airplane Flight Manual 
(AFM) Supplement CR102-F-066, Change 19, dated October 2, 1997 (for 
Boeing 727QF airplanes), which prohibits stabilized operation between 
60 and 75 percent N1 speed during ground operations in reverse or 
forward thrust. Accomplishment of the actions specified in the service 
document is intended to adequately address the identified unsafe 
condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Boeing Model 727-100 series airplanes of this 
same type design registered in the United States, this AD is issued to 
require a revision to the Limitations Section of the FAA-approved AFM 
to prohibit stabilized operation between 60 and 75 percent N1 speed 
during ground operations in reverse or forward thrust.
    These actions are required to be accomplished in accordance with 
the document described previously.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire.

[[Page 59566]]

 Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 97-NM-268-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

97-23-02  Boeing: Amendment 39-10190. Docket 97-NM-268-AD.

    Applicability: Model 727-100 series airplanes modified in 
accordance with Supplemental Type Certificate (STC) SA8472SW, which 
includes installation of Rolls-Royce Tay 651-54 engines; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent uncontained failure of engine fan blades due to high 
cycle fatigue cracking, which could result in loss of thrust from 
the affected engine and secondary damage to the airplane and/or 
fire, accomplish the following:
    (a) Within 72 hours after the effective date of this AD, revise 
the Limitations Section of the FAA-approved Airplane Flight Manual 
(AFM) by inserting a copy of Dee Howard Airplane AFM Supplement 
CR102-F-066, Change 19, dated October 2, 1997, in the AFM.
    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Airplane Certification Office, ASW-
150, FAA, Rotorcraft Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, Airplane 
Certification Office, ASW-150.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Airplane Certification Office, ASW-150.
    (c) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.
    (d) The AFM revision shall be done in accordance with Dee Howard 
Airplane Flight Manual Supplement CR102-F-066, Change 19, dated 
October 2, 1997 (for Boeing 727QF airplanes), which contains the 
following list of effective pages.

                                                                        
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                                    Revision level                      
           Page number               shown on page    Date shown on page
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Title Page......................  19................  November 25, 1992.
1-1, 1-3, 3-4, 3-15, 4-61.......  Not Shown.........  October 2, 1997.  
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    The incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from the Dee Howard Company, P.O. 
Box 469001, San Antonio, Texas 78246. Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Rotorcraft Directorate, 2601 Meacham 
Boulevard, Fort Worth, Texas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on November 19, 1997.

    Issued in Renton, Washington, on October 29, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-29114 Filed 11-3-97; 8:45 am]
BILLING CODE 4910-13-U

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