[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48620-48623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19834]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0761; Directorate Identifier 2010-NM-069-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This proposed AD would require installing two warning level
indicator lights on the P2-2 center instrument panel in the flight
compartment for certain airplanes. For a certain other airplane, this
proposed AD would require activating the cabin altitude warning and
takeoff configuration warning lights. For all airplanes, this proposed
AD also would require revising the airplane flight manual to remove
certain requirements included by previous AD actions, to require new
pressure altitude limitations for certain airplanes, and to advise the
flightcrew of the following changes: revised emergency procedures to
use when a cabin altitude warning or rapid depressurization occurs, and
revised cabin pressurization procedures for normal operations. This
proposed AD results from a design change in the cabin altitude warning
system that would address the identified unsafe condition. We are
proposing this AD to prevent failure of the flightcrew to recognize and
react to a valid cabin altitude warning horn, which could result in
incapacitation of the flightcrew due to hypoxia (lack of oxygen in
body), and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by September 27,
2010.
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 proposed 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 [email protected];
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 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.
[[Page 48621]]
FOR FURTHER INFORMATION CONTACT: Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6472; fax (425) 917-6590.
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-2010-0761;
Directorate Identifier 2010-NM-069-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
The Model 737 cabin altitude warning is an intermittent horn that
sounds when cabin altitude exceeds 10,000 feet. The same intermittent
warning horn sound is utilized by the takeoff configuration warning
system (TCWS) to warn of unsafe airplane configuration for takeoff. The
TCWS warning functionality is inhibited by air/ground logic when the
airplane is in flight. However, the Model 737 cabin altitude warning
system design does not currently incorporate a dedicated means of
positively identifying the warning horn as a cabin altitude warning or
a takeoff configuration warning. There are approximately 25 known
instances where flightcrews have misinterpreted a valid cabin altitude
warning as a takeoff configuration warning.
Failure of the flightcrew to recognize and react to a valid cabin
altitude warning horn could result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body), and consequent loss of control
of the airplane. To address this unsafe condition, we issued the
following ADs.
On November 7, 2003, we issued related AD 2003-03-15 R1, Amendment
39-13366 (68 FR 64802, November 17, 2003), for various The Boeing
Company and McDonnell Douglas Corporation transport category airplanes.
That AD requires revising the airplane flight manual (AFM) to advise
the flightcrew to don oxygen masks as a first and immediate step when
the cabin altitude warning occurs. We issued that AD to prevent
incapacitation of the flightcrew due to lack of oxygen, which could
result in loss of control of the airplane.
On June 15, 2006, we issued related AD 2006-13-13, Amendment 39-
14666 (71 FR 35781, June 22, 2006). (A correction of that AD was
published in the Federal Register on July 3, 2006 (71 FR 37980).) That
AD applies to all Model 737 airplanes. That AD requires revising the
AFM to advise the flightcrew of improved procedures for pre-flight
setup of the cabin pressurization system, as well as improved
procedures for interpreting and responding to the cabin altitude/
configuration warning horn. That AD resulted from reports that
airplanes had failed to pressurize, and that the flightcrews failed to
react properly to the cabin altitude warning horn. We issued that AD to
prevent failure of the airplane to pressurize and subsequent failure of
the flightcrew to recognize and react to a valid cabin altitude warning
horn, which could result in incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body) and consequent loss of airplane
control.
On October 24, 2008, we issued related AD 2008-23-07, Amendment 39-
15728 (73 FR 66512, November 10, 2008), for all Model 737 airplanes.
That AD requires revising the AFM to include a new flightcrew briefing
that must be done before the first flight of the day and following any
change in flightcrew members, and to advise the flightcrew of this
additional briefing. That AD resulted from continuing reports that
flightcrews have failed to recognize and react properly to the cabin
altitude warning horn. We issued that AD to prevent failure of the
flightcrew to recognize and react properly to a valid cabin altitude
warning horn, which could result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body) and consequent loss of airplane
control.
The preambles to AD 2006-13-13 and AD 2008-23-07 explain that the
revisions to the AFM required by those ADs are considered to be interim
action. The manufacturer had advised us that it was developing a design
change in the cabin altitude warning system that would address the
identified unsafe condition(s), and that once this design change was
developed, approved, and available, the FAA might consider additional
rulemaking. The manufacturer now has developed such a modification, and
we have determined that further rulemaking is necessary; this proposed
AD follows from that determination. We can better ensure long-term
continued operational safety by modifications or design changes to
remove the source of the problem, rather than by AFM revisions alone.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-31A1325, dated
January 11, 2010 (for Model 737-100, -200, -200C, -300, -400, and -500
series airplanes). This service bulletin describes procedures for
installing two warning level indicator lights on the P2-2 center
instrument panel in the flight compartment. This installation includes
changing three wire bundles.
We have also reviewed Boeing Alert Service Bulletin 737-31A1398,
dated January 7, 2010 (for Model 737-400 series airplane, variable
number PW234). This service bulletin describes procedures for
activating the cabin altitude warning and takeoff configuration warning
lights. The activation includes changing the wiring in the W066 wire
bundle and removing the INOP markers from the cabin altitude warning
and takeoff configuration warning lights.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously. The proposed AD would
also require revising the AFM to remove certain requirements included
by previous AD actions, to require new pressure altitude limitations
for certain airplanes, and to advise the flightcrew of the following
changes: revised emergency procedures to use when a cabin altitude
warning or rapid depressurization occurs, and revised cabin
pressurization procedures for normal operations.
Costs of Compliance
We estimate that this proposed AD would affect 741 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
[[Page 48622]]
Table--Estimated Costs
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Number of
Average labor Cost per U.S.-
Action Work hours rate per hour Parts product registered Fleet cost
airplanes
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Installation of warning indicator lights................ 20 $85 $2,738 $4,438 740 $3,284,120
Activation of the cabin altitude warning system/takeoff 1 85 0 85 1 85
configuration warning lights...........................
AFM revision............................................ 1 85 0 85 741 62,985
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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.
You can find our regulatory evaluation and the estimated costs of
compliance 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0761; Directorate Identifier
2010-NM-069-AD.
Comments Due Date
(a) We must receive comments by September 27, 2010.
Affected ADs
(b) This AD affects the ADs identified in paragraphs (b)(1),
(b)(2), and (b)(3) of this AD. This AD does not supersede the
requirements of these ADs.
(1) AD 2008-23-07, Amendment 39-15728.
(2) AD 2006-13-13, Amendment 39-14666.
(3) AD 2003-03-15 R1, Amendment 39-13366.
Applicability
(c) This AD applies to the airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) The Boeing Company Model 737-100, -200, -200C, -300, -400,
and -500 series airplanes identified in Boeing Alert Service
Bulletin 737-31A1325, dated January 11, 2010.
(2) The Boeing Company Model 737-400 series airplanes identified
in Boeing Alert Service Bulletin 737-31A1398, dated January 7, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 31:
Instruments.
Unsafe Condition
(e) This AD results from a design change in the cabin altitude
warning system that would address the identified unsafe condition.
The Federal Aviation Administration is issuing this AD to prevent
failure of the flightcrew to recognize and react properly to a valid
cabin altitude warning horn, which could result in incapacitation of
the flightcrew due to hypoxia (lack of oxygen in body) and
consequent loss of airplane control.
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.
Installation of Warning Indicator Lights
(g) For airplanes identified in Boeing Alert Service Bulletin
737-31A1325, dated January 11, 2010: Within 36 months after the
effective date of this AD, install two warning level indicator
lights on the P2-2 center instrument panel in the flight
compartment, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-31A1325, dated January 11, 2010.
Activation of Warning Indicator Lights
(h) For airplanes identified in Boeing Alert Service Bulletin
737-31A1398, dated January 7, 2010: Within 36 months after the
effective date of this AD, activate the cabin altitude warning and
takeoff configuration warning lights, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
31A1398, dated January 7, 2010.
Airplane Flight Manual (AFM) Revisions
(i) Before further flight after doing the installation or
activation of the warning lights required by paragraph (g) or (h) of
this AD, do the actions specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD.
(1) Revise the Limitations Section of the applicable Boeing 737
AFM by doing the actions specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD.
(i) Delete the ``CABIN ALTITUDE WARNING TAKEOFF BRIEFING'' added
by AD 2008-23-07.
(ii) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``For airplanes approved for maximum takeoff and landing
altitudes above 8,400 feet pressure altitude, change the limitation
for Maximum Takeoff and Landing pressure altitude as follows: With
the CABIN ALTITUDE and TAKEOFF CONFIG lights installed and operative
on those airplanes without the High Altitude Landing switch
installed, maximum takeoff and landing altitude is limited to 9,000
feet pressure altitude.''
[[Page 48623]]
(2) Revise the Emergency Procedures Section of the applicable
Boeing 737 AFM by doing the actions specified in paragraphs
(i)(2)(i), (i)(2)(ii), (i)(2)(iii), and (i)(2)(iv) of this AD.
(i) Delete the procedure ``WARNING HORN--CABIN ALTITUDE OR
CONFIGURATION'' added by AD 2006-13-13.
(ii) Delete the procedure entitled ``CABIN ALTITUDE WARNING OR
RAPID DEPRESSURIZATION'' added by AD 2006-13-13.
(iii) If the procedure entitled ``CABIN ALTITUDE (Airplanes with
the CABIN ALTITUDE lights installed)'' is currently contained in the
applicable Boeing 737 AFM, delete the procedure entitled ``CABIN
ALTITUDE (Airplanes with the CABIN ALTITUDE lights installed).''
(iv) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``CABIN ALTITUDE WARNING OR RAPID DEPRESSURIZATION (required by
this ad)
Condition: The CABIN ALTITUDE warning light illuminates or the
intermittent warning horn sounds in flight above 10,000 ft MSL.
RECALL:
Oxygen Masks and Regulators............ On, 100%
Crew Communications.................... Establish
REFERENCE:
Pressurization Mode Selector........... Manual
Outflow Valve Switch................... Close
Passenger Oxygen (If Required)......... On
Descent (If Required).................. Initiate
(3) Revise the Normal Procedures Section of the applicable
Boeing 737 AFM by doing the actions specified in paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD.
(i) Delete the ``CABIN ALTITUDE WARNING TAKEOFF BRIEFING''
procedure added by AD 2008-23-07.
(ii) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``For normal operations, the pressurization mode selector should
be in AUTO prior to takeoff. (Required by this AD)''
Note 1: When statements identical to those specified in
paragraphs (i)(1)(ii), (i)(2)(iv), and (i)(3)(ii) of this AD have
been included in the general revisions of the AFM, the general
revisions may be inserted into the AFM, and the copies of this AD
may be removed from the AFM.
Terminating Action for Affected ADs
(j) Accomplishment of the requirements of this AD terminates the
specified requirements of the ADs identified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD, for only the airplanes identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) AD 2008-23-07: All requirements of that AD.
(2) AD 2006-13-13: All requirements of that AD.
(3) AD 2003-03-15 R1: The requirements specified in paragraph
(a), Table 2, and Figures 2 and 3 of that AD.
Special Flight Permit
(k) Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
Alternative Methods of Compliance (AMOCs)
(l)(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. Send information to
ATTN: Jeffrey W. Palmer, Aerospace Engineer, Systems and Equipment
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6472; fax (425) 917-6590. Information may be e-mailed to: [email protected].
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Issued in Renton, Washington, on July 28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-19834 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P